Post Stall Wind Tunnel Data for NACA

SERI/STR-217 -2559 UC Category: 60 DE85002948

Post-Stall Wind Tunnel Data for NACA 44XX Series Airfoil Sections A Subcontract Report

C. Ostowari

D. Naik

January 1985

Prepared under Subcontract No. ASC-78348PB of Rockwell International Corp.

Final Reportprepared under SERI Task No. 4807.20 FTP No. 495

SERI Technical Monitor: James Tangier

Solar Energy Research Institute A Division of Midwest Research I nstitute

1617 Cole Boulevard

Golden, Colorado 80401

Prepared for the

U.S. Department of Energy Contract No. DE-AC02-83CH10093

:iE:�I .� ----------------------------------------------------------------�S�T_R_-_2

_5_· 5�, 9

PREFACE

This report was prepared by c. Ostowari and D. �aik under Subcontract No. ASC-78348PB for Rockwell International Corporation's Wind Energy Research Center under their contract No. DE-AC04-76DP03533. As of October 1, 1984, the Wind Energy Research Center is under the operation of the Solar Energy Research Institute, which coordinated the publication of this report under Task No. 4807 . 20.

Approved for

J. T�gler Project Manager

SOLAR ENERGY RESEARCH INSTITUTE

A. Trenka, l'lanager \Vind Systems Program Hanagement

�!) R' h' D--.

� -- ��----------• 1tc 1e, 1rector

Solar Electric Research Division

s;::�l I�I-------------------------------------------------------S_T_R_-_2_5_5 __ 9

ACKNOWLEDGEMENT

The authors wish to express their appreciation for the support of this project by Rockwell International, especially J. Tang ler of the Wind Energy Research Staff.

Our sincere thanks to P. K. Imbrie of the Texas A&M Low Speed Wind Tunnel Facility for his help during the tests.

STR-25 5 9

SUMMARY

Obj ective

To characterize the performance of a nonrotating blade in stall as a function of its aspect ratio, airfoil thickness, and Reynolds number.

Discussion

Wind- turbine blades operate over a wide angle of attack rang e. Unlike aircraft, a wind turbine's angle of attack range extends deep into stall where the three-dimensional performance characteristics of airfoils are not generally known. Peak power predictions upon which wind turbine components are sized depend on a g ood understanding of a blade's post-stall characteristics.

This report documents results of the wind tunnel investig ation of constant chord nonrotating blades having four aspect ratios, with NACA 44XX series airfoil sections, at ang les of attack rang ing from -100 to uoo. Tests were conducted at Reynolds numbers rang ing from 0.25 x 106 to 1.0 x 106. The thickness ratios studied were 0.18, 0.15 , 0.12, and 0.09 . The aspect ratios were 6, 9 , 12, and infinity.

Results of force and pitching moment measurements over the angle of attack range, for all combinations of Reynolds number, thickness, and aspect ratios, and the effects of boundary layer tripping are presented.

Conclusions

The lift and post-stall drag coefficients decrease with decreasing aspect ratio. The lift coefficient decreases with decreasing thickness ratio while the drag coefficient increases. In the post-stall region both lift and drag coefficient are relatively insensitive to Reynolds number effects and the range tested. The boundary layer tripping decreases the lift curve slope and stalling angle of attack. The drag coefficient (with tripping) is significantly affected only at low aspect ratio.

1'ABLE OF OONTENTS

Introduction • • ...• • ........• • ........• ..• ..• .• ....• ......• • ..• ..• ..•

Experimental Set-UP• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • 2.1 Wind Tunnel Description • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • 2.2 Model Description• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • .........

Test Procedure• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • 3.1 Test Conditions .• • • • • • .• • • • • • .• • • • • • • • • • • • • • • • • • • • • • • • • • • • • .• • • 3.2 Procedure• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •

and Discussion .• .• .• • • • • • • • • .• • • • • • • • • • • • • • • • • • • • ..• • • .• • • • . Results 4.1 NACA 4.2 4.3 4.4 4.5 4.6 4.7

4418 NACA 4415 NACA 4412 NACA 4409 NACA 4415 Effect of Effect of

Section ....• • .• ..• ..• ..• • ..• • • .• • • • • • • • • • • • • • • ..• • • • . Section • ..• ..• .• .• .• • • .• • • • • • • .• .• • • • • • • .• .• ..• • • .• • . Section .• .• • • • ....• • • • .• .• ..• .• • .• .• • • • • • • ..• • .• • • • • . Section • • • • • • • .• .• • .• • • • • • • • • • • • • • • • • • • .• • • • • .• • • • • • • Section with Boundary Layer Tripping • • • • • • • • • • • • • • • • • Aspect Ratio • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • Air foil Thickness• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •

Conclusions• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •

References • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •

Appendix A Force and Moment Data• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •

12 12 12

15 15 16 16 16 16 17 17

Appendix B Wake Rake Drag Estimation• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • 167

- iltalllm 5-�1 �"'· STR-2559 - �

LIST OF TABLES

2-1 Instrument Resolution . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . . . . . . • . • . . . • . .

3-1 Test Condit ions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3-2 Sumtnary of Figures . . . . . . . . . . . . . . . . . . . . . . . • . • . . . . • . . . . . . . . . . . . • . . •

LIST OF FIGURES

2-1 Schematic of the Texas A&M 2.31-m by 3. 05-m Low Speed Wind

Tunnel. . . . . . . . . . . . . . . . . . . . . . . . . • • . • . . . . . . . . . . . . . . . . . . . . . . . . • • . . . . . • 3

2-2 Blade Model Mounted in the Wind Tunnel Test Section • • • • • • • • • • • • • • • • 4

2-3 Airfoil Coordinates (a) NACA 4418 Section • • • . . . . . . . . . . . . . . . . . . . . 5 (b) NACA 4415 Section • • • . . . . . . 6 (c) NACA 4Ld 2 Section • • • . . . . . . . . . . . 7 (d) NACA 4409 Sec tion • • • . . . . . . . . . 8

2-4 NACA 4415 Section Model with Boundary Layer Trip Strips • • • • • • • • • • • • 10

2-5 Cross-Sectional View Showing the Model Construction • • • • • • • • • • • • • • • • 11

A. 1 through A. 63 . . • . . . • . . . . . . . . . . . . . . . . . . • . . . . . . . . . • . . . . . . . . . . . . . 21 to 165

B.l throt1gh B.4 . . . • • • . . • . • • • . • • • . • • • . • • . • . • . . • . . • . • . . • . • • . . . . . . . • 168 to 171

s=�·'*' ---------------------------'S�T�R�-=..25.!,_,5LL9

NOMENCLATURE

The force and the airfoil. made in U.S. may be found

moment data have been re ferred to the quarter-chord location on Dimensional quantities are given in SI units. Measurements were Customary Units. Conversion factors between the various units

in Ref. 2.

AR aspect ratio

b span

c airfoil reference chord

drag coefficient

lift coefficient

drag/( dynamic pressure x area)

lift/( dynamic pressure x area)

RN s t

pitching moment coefficient with respect to the 0 .25 c location = moment/( dynamic pressure x area x c)

Mach number

dynamic pressure

Reynolds number

wing area

airfoil maximum thickness

free stream velocity

angle of attack

· STR-2559 s=�1 ,;.�, -------------------------------------- ·��

SECTION 1.0

INTRODUCTION

Current research efforts are direc ted toward t he design of cost-effective wind energy conversion devices. The accomplishment of this goal requires good rotor-t o-load matching. Proper matching depends on an accurate knowledge of the post-stall airfoil characteristics, upon which peak power predic tion is strongly dependent.

Contemporary wind turbine blades are typical ly of high aspect ratio for costeffective, high RPM opera tion. The blade sections are subjected to a large range of angles of at tack for which, particularly at post-stal l conditions, aerodynamic data are l acking. This report a t t empts to fill part of t his airfoil dat a void and present s the post -stall aerodynamic characteristics as a function of aspect ratio, airfoil thickness, and Reynolds number. Aspect ratios of 6, 9, 12, and infinit y were tested using const ant chord blades over the angle of at tack range of -180 to 1100. One airfoil series ( NACA 44XX) having four different thicknesses ( 18%, 15%, 12%, and 9%) was investigated. The tests were conducted for Reynolds numbers ( with respect to blade chord) of 0.25 X 106, 0.50 X 106, 0.75 X 106, and 1.0 X 106.

Also presented is t he effect of boundary layer t ripping on the aerodynamic charac teristics of the NACA 4415. Tripping was achieved by applying chart tape at selected chord locations on the blade's upper and lower surfaces. This roughly simulates an unclean blade tha t has been struck by insects, grit, and bird droppings [1].

The tests were conduc ted at the Texas A&M University Low Speed Wind Tunnel Facility in July 1983. The blade performance charac teristics presented in t his report are lift coefficient, drag coefficient, and pitching moment coefficient versus angle of a t t ack.

5;==�1 I�I--------------------------------------------------------�S�T�R_-;2�5�5�9 - ,§�

SECTION 2.0

EXPERIMENTAL SET-UP

2.1 WIND TUNNEL DESCRIPTION

A schematic of the Texas A&M 2.13-m x 3.05-m Low Speed Wind Tunnel is given in Figure 2-1. It is a closed circuit, single return type tunnel. The main balance of the tunnel is a six-component, pyramidal, virtual center external balance. The resolution of the various instrumentation systems is given in Table 2-1.

Table 2-1. Instrument Resolution

Measurement Resolution

Dimensional form Coefficient form*

Lift ( balance) Drag (balance) Pitch moment ( balance) Angle of attack Dynamic pressure

±1. 78 N ±0.89 N ±0.27 Nm ±0.1 ° ±0.4%

*For infinite aspect ratio blades.

probable

±0.0002 ±0.0001 ±0.00003

maximum

±0.0034 ±0.0017 ±0.0005

A Perkin-Elmer 8/ 16 E minicomputer is used for data acquisition and for reduction of final data and plots. More details of the facility may be found in Ref. 3.

2.2 MODEL DESCRIPTION

The models used were of the reflection plane type. This provides an effective aspect ratio that is twice the model aspect ratio. Each model extended into the tunnel section from an external-balance mount that was flush with the tunnel floor ( Figure 2-2) . All models were of the NACA 44XX family of airfoils. The thickness ratios studied were 0.18, 0.15, 0.12, and 0.09. The four airfoil section geometries are given in Figures 2-3a-d.

For tests in the Texas A&M facility, the models were sized with a 2.13-m span and a 0.305-m chord. This corresponds to a blade with infinite aspect ratio when placed in the 2.13-m x 3.05-m tunnel section. Effective aspect ratios of

48.46 m

w 12.19 m

3.05 m r---:--1 $�2.31 m

Figure 2-1. Schematic of the Texas A&M'2.3l-m by 30.5-m Low Speed Wind Tunnel (adapted from Ref. 3)

Ul Ill N -

!.1 §�

U) rl ;;o I N U1 U1 \,C

s=��-� ---------------------------=-ST=-=R-=----==2.:::.,5�59 .

Figure 2-2. Blade Model Mounted in the Wind Tunnel Test Section

STR-2559

x/c Y/C yl/c 0 001()()() '-' 008536 -0. 008136

0 00 2000 0 012121 -o. 011323

0 OOJOOO 0 014890 -o .013695

0 00� 000 0 017237 -o .015645

0 005000 0 019313 - o .017326

0 OOGOOO 0 021197 -o .018815

0 00101)0 0 022935 -o 020159

() 008000 0 024557 -o .021389

0 .009000 0 026083 -0.022524

0 010000 0 027531 -0.023581

0 011000 0 028910 -0.024570

0 012000 0 030229 -0.025501

0 013000 0 031497 -0.026382

0 014000 0 032719 -0.027217

0 015000 0 033899 -o. 028011

0 016000 0 035041 -0.028769

0 017000 0 036150 -0.029494

0 018000 0 .037227 -0.030189

0 019000 0 .038275 -0.030855

0 020000 0 039297 -0.031497

0 . 02 1000 0 040294 -0.032114

0 .022000 0. 041267 -0.032709

0 02 3000 0 .042220 -o .033284

0 024000 0 043152 -o 033840

0 025000 0 044065 -o. 034377

0 050000 0 062695 -o .043945

0 075000 0 076592 -o .049405

0. 100000 0 08774 1 -o. 05274 1

0 125000 0 096925 -0. 054737

() 150000 0 104552 -o .055802

0 175000 o. 110875 -0.056188

0 2 00000 o. 1 16063 -0.056063

0 2 75000 o. 120238 -0.055550

0 ?50000 0 123493 -0.054743

0 2"15000 0 125903 -o .053715

0 100000 0 127526 ··0 .052526

0 32 5000 0 1284 12 -0 .051225

0 350000 0 128604 -o .049854

0. :)75000 0 128138 -o .048450

0 •100000 0 127045 - o .047045

0 ·1?50()0 0 125440 -o .045579

1.) 45oory) 0 123433 -o .043989

0 -175000 o. 12 1047 -o 042297

0 500000 0 I I 8299 - o .040521

0 575000 0 1 15208 -o .038680

0 ssooon 0 111786 -o .036786

0 575000 0 1080·19 -0. 034854

() CJOr)QOO 0 104006 -0.032895

() G:?sono 0 099668 -0.030918

0 G:)oooo 0 095043 -o .028932

u G75000 0 090138 -o .026943 1) 70()0()0 0 084959 -o .024959

0 nsooo 0 079509 -0.022982

() 750000 0 073794 -0.021016

0 775000 0 .067813 -0.019063

0. 800000 0 061569 -0.017125

0 825000 0 055061 -0.015200

0 850000 0 048288 -o .013288

0 875000 0 041248 -o. 011387

0 gooooo 0 033938 -o .009494

" 9:J5Q(_)() 0 026353 -0. 007603

() :1S0000 0 018487 -o .005710

() 9750�'() 0 010336 -o .003808

1 onoooo 0 001890 -0. 001890

Figure 2-3a. NACA 4418 Airfoil Coordinates

/.� STR-2559 5= .... 51 11.11 -------------------=-=-=--=-=� ��

x/c 0. 001000 0.002000 0.003000 0.004000 0.005000 0.006000 0.007000 0.008000 0.009000 0.010000 0.011000 0.012000 0.013000 0.014000 0.015000 0.016000 0.017000 0.018000 0.019000 0.020000 0.021000 0.022000 0.023000 0.024000 0.025000 0.050000 0.075000 0. 100000 0.125000 0.150000 0. 175000 0. 200000 0.225000 0.250000 0.275000 0. 300000 0.325000 0.350000 0.375000 0.400000 0.425000 0.450000 0.475000 0. 500000 0.525000 0.550000 0.575000 0.600000 0.625000 0.650000 0.675000 0.700000 0.725000 0. 750000 0. 775000 0.800000 0.825000

0.850000 0.875000 0.900000 0.925000 0.950000 0.975000 I .000000

Figure 2-3b.

Y/C yl/c 0.007147 -0.006747 0.010167 -0.009369 0.012508 -0.011313 0.014497 -0.012905 0.016260 -0.014273 0.017863 -0.015481 0.019344 -0.016568 0.020728 -0.017560 0.022033 -0.018473 0.023271 -0.019321 0.024453 -0.020113 0.025585 -0.020857 0.026674 -0.021558 0.027724 -0.022222 0.028740 -0.022852 0.029724 -0.023452 0.030679 -0.02

0.031609 -0.024571 0.032514 -0.025095 0.033397 -0.025597 0.034260 -0.026080 0.035103 -0.026545 0.035928 -0.026992 0.036736 -0.027424 0.037528 -0.027840 0.053808 -0.035059 0.066092 -0.038905 0.076034 -0.041035 0.084286 -0.042099 0.091189 -0.042439 0.096953 -0.042266 0. 101719 -0.041719 0. 105589 -0.040901 0. 108640 -0.039890 o. 110935 -0.038747 0. 112521 -0.037521 0.113442 -0.036255 0.113733 -0.034983 0.113422 -0 033735 0.112537 -0.032538 0.111188 -0.031327 0.109481 -0.030037 0.107435 -0.028685 0. 105064 -0.027286 0.102384 -0.025856 0.099405 -0.024405 0.096140 -0.022946 0.092598 -0.021487 0.088786 -0.020036 0.084712 -0.018601 0.080381 -0.017187 0.075799 -0.015799 0.070968 -0.014441 0.065893 -0.013115 0.060573 -0.011823 0.055011 -0.010567 0.049206 -0.009345

0.043157 -0.008157 0.036862 -0.007001 0.030319 -0.005874 0.023523 -0.004773 0.016471 -0.003693 0.009157 -0.002629 0.001575 -0.001575

NACA 4415 Airfoil Coordinates

STR-2559

�� C__ __ _______.---------------------�--------�----= x/c Y/C yl/c

0 .00 0 0 0.0

0 005000 o. 013207 -0.011219

0 006000 0 .014528 -0.012146

0 007000 0 .015753 -0.012977

0 008000 o. 016899 -0.013731

0 009000 0 017982 -0.014423

0 010000 0.019012 -0.015062

0 011000 0 .019996 -0.015657

0 012000 0 .020941 -0.016213

0 013000 o. 021851 -0.016735

0 .014000 0 .022729 -0.017228

0 015000 0 .023580 -0.017693

0 . 016000 0.024406 -0.018134

0 .017000 0.025209 -0.018554

0 . 018000 0.025991 -0.018953

0 019000 0.026753 -0.019334

0 .020000 0.027498 -0.019698

0 .021000 0 .028226 -0.020046

0 022000 0. 028938 -0.020380

0 023000 0 .029636 -0.020700

0 024000 0.030320 -0.021008

0 .025000 0.030991 -0.021303

0 050000 0 .044922 -o. 026112

0 075000 0 055593 -0.028405

0 . 100000 0. 064328 -0.029328

0 125000 0 .071648 -0.029460

0 . 150000 0. 077826 -0.029076

0 . 175000 0 083031 -0.028344

0 .200000 0 .087375 -0.027375

0. 225000 0. 090940 -0.026252

0 250000 0 .093787 -0.025037

0 275000 0 095966 -0.023779

0. 300000 0 .097517 -o. 022511

0. 325000 0 .098473 -0.021285

0 . 350000 0 .098861 -0.020111

0 375000 0 .098706 -0.019019

0 400000 0 .098030 -0 .018030

0 �25000 0 096937 -0.017076

0 . 450000 0.095529 -0.016085

0 . 475000 0.093823 -0.015073

0 500000 0.091829 -0.014051

0 525000 0.089560 -0.013032

0 550000 0.087024 -0.012024

0 575000 0. 084232 -0. Of 1037

0 600000 0.081189 -0. 010078

0 . 625000 0 .077904 -0.009154

0 .650000 0 . 074380 -0.008269

0. 675000 0 .070624 -0.007430

0 700000 0.066639 -0.006639

0. 725000 0.062428 -0.005900

0. 750000 0.057992 -0.005214

0 775000 0.053334 -0.004584

0 .800000 0.048453 -0.004009

0. 825000 0.043351 -0.003490

0. 850000 0.038026 -0.003026

0. 875000 0.032476 -0.002615

0 900000 0. 026699 -0.002255

0 . 925000 0.020693 -0.001943

0 . 950000 0.014455 -0.001677

0 . 975000 0.007978 -0.001451

1 000000 0.001260 -0.001260

Figure 2-3c. NACA 4412 Airfoil Coordinates

�, STR-2559 !:iE:�I ��;' --------------------------------------------------------------------------��--��

x/c o.oc 0.005000 0.006000 0.007000 0.008000 0.009000 0.010000 0.011000 0.012000 0.013000 0.014000 0.015000 0.016000 0.017000 0.018000 0.019000 0.020000 0.021000 0.022000 0.023000 0.024000 0.025000 0.050000 0.075000 o. 100000 0. 125000 o. 150000 0. 175000 0.200000 0.225000 0.250000 0.275000 0.300000 0.325000 0.350000 0.375000 0. 400000 0.425000 0. 450000 0. 475000 0.500000 0.525000 0.550000 0.575000 0.600000 0.625000 0.650000 0.675000 0. 700000 0.725000 0.750000 0.775000 0.800000 0.825000 0.850000 0.875000 0.900000 0.925000 0.950000 0.975000 1. 000000

Figure 2-3d.

0.00 0.010154 0.011194 0.012161 0.013070 0.013932 0.014753 0.015540 0.016297 0.017027 0.017735 0.018421 0.019089 0.019739 0.020373 0.020992 0.021598 0.022192 0.022773 0.023344 0.023904 0.024454 0.036035 0.045093 0.052621 0.059009 0.064464 0.069109 0.073031 0.076291 0.078934 0.080998 0.082513 0.083503 0.083990 0.083991 0.083522 0.082665 0.081578 0.080211 0.078594 0.076736 0.074643 0.072323 0.069761 0.067021 0.064049 0.060868 0.057479 0.053887 0.050091 0.046094 0.041896 0.037496 0.032894 0.028090 0.023080 0. 017864 0.012438 0.006800 0.000945

0.00 -0.006 -0.008812 -0.009386 -0.009902 -0.010372 -0.010803 -0.011200 -0.011569 -0.011912 -0.012233 -0.012534 -0.012817 -0.013083 -0.013335 -0.013573 -0.013798 -0.014012 -0.014215 ··0.014408 -0.014592 -0.014767 -0.017285 -0.017905 -0.017621 -0.016822 -0.015714 -0.014422 -0.013032 -0.011603 -0.010184 -0.008811 -0.007513 -0.006315 -0.005240 -C.004303 -0.003523 -0.002824 -0.002133 -0.001461 -0.000816 -0.000208

0.000357 0.000871 0.001330 0.001728 0.002062 0.002327 0.002521 0.002641 0.002687 0.002656 0,002549 0.002365 0.002106 0.001772 0.001364 0.000886 0.000340

-0.000272 -0.000945

NACA 4409 Airfoil Coordinates

s=�·'*' ------------------------....::::;S-=..:TR:..=...--=2=5.=:-=:.5 9

12, 9, and 6 were obtained by cutting the models at appropriate span locations. Angle of attack variation was achieved through rotation of the turntable built into the tunnel floor. This turntable rotates with the external balance but is isolated from it. For boundary layer trip studies, the NACA 4415 model was fitted with transition strips located at 5% chord on the upper surface and at 10% chord at the lower surface. The transition strips were two layers of 0.127-mm-thick and 2.36-mm-wide chart tape. This is shown in Figure 2-4.

The airfoils were fabricated from 12.7-mm Douglas fir vertical laminates bonded with wood glue. Figure 2-5 shows the bonding for the four airfoil sections. The blade lower ends were shaped to facilitate attachment to the balance mount. Care was taken to ensure that this bulge did not protrude into the tunnel section. Further, the 0.25 chord location was used as a reference point for model mounting to minimize the error in moment transfer.

SE�II*I ------------------------'--ST=R.;._-__;2 5�59

Figure 2-4. NACA 4415 Section Model with Boundary Layer Trip Strips

,_. ......

Figure 2-5. Cross-Sectional View Showing the Model Construction

Ul Ill N -

•=, II II '\: �'/

(./) � :;>;::� I N ln ln \.0

5iE:�I �� ----------------------------------------------------------------��

SECTION 3.0

TEST PROCEDURE

3.1 TEST CONDITIONS

The models were tested at the conditions given in Table 3-1.

Table 3-1. Test Conditions

Dynamic Pressure (N/m2)

71.82 277.7 627.23

1110.82

Reynolds Number* ( X 10-6)

0.25 0.50 0.75 1.00

Mach Number

0.05 0.09 0.14 0.19

*The Reynolds number is with respect to airfoil chord.

3.2 PROCEDURE

Section drag measurements were made with the wake rake apparatus for all four infinite aspect ratio blades. Wake rake surveys were made at four different Reynolds numbers with the angle of attack ranging from -10° to 12° in 2° increments. The wake rake was located one chord length behind the model trailing edge.

Force measurements were made for 19 blade configurations (4 aspect ratios, each with 4 airfoil thickness; 3 with trip strips on NACA 4415) at the 4 different Reynolds numbers given above and for angles of attack ranging from -10° to 110°. Table 3-2 summarizes the various measurements and cross plots presented in this report. The three component force masurements were made using the wind tunnel main balance system.

The difference between the force balance drag measurement and wake rake drag estimate is the end-plate and interference drag with the tunnel floor and ceiling, which depends on both the lift coefficient and the section geometry. The wake survey method cannot be used when flow separation is present, so it was not applied to high angles of attack. Under high drag conditions, however, the end-plate tare and interference tare are a relatively small portion of the total drag. Therefore, the tare curve is extrapolated for high lift coefficient conditions and is generally assumed constant past a lift coefficient of roughly 1.3.

All data were corrected for tunnel-wall effects (wake blockage, solid blockage, buoyance drag, etc. ) using the. standard procedure given in Ref. , 1.

s-�� - ll(IIJI) - ·��

Tunnel Hodel Airfoils NACA 4415 Airfoils NACA 4418, NACA 4418 , NACA 4418 , NACA 4418 , NACA 4415 , NACA 4415 , NACA 4415 , NACA 4415 , NACA 4412, NACA 4412, NACA 4412, NACA 4412, NACA 4409, NACA 4409, NACA 4409, NACA 4409, NACA 4415, NACA 4415 , NACA 4415 , NACA 4415 , NACA 4415, NACA 4415 , NACA 4415, NACA 4415 , NACA 4415, NACA 4415 , NACA 4415 , NACA 4415 , NACA 4415 , NACA 4415 , NACA 4415 , NACA 4418 , NACA 4418, NACA 4418 , NACA 4418, NACA 4415 , NACA 4415, NACA 4415 , NACA 4415, NACA 4412, NACA 4412,

Table 3-2. Summary of Figures

Configuration

AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR AR RN RN RN RN RN RN RN RN RN RN

12 9 6

= co = 12

= co 12

12, 6,

co, = co

12, 12, 12, 12,

6, 6, 6, 6,

0.25 0.5 0 0.75 1.00 0.25 0. 50 0.75 1.00 0.25 0.50

Trip Trip Trip RN RN RN RN RN RN RN RN RN RN RN RN

miL mil. mil. mil. miL mil. mil. mil. mil. mil.

Type Data

Schematic Model mount Model geometry Transition strips Model construction CL, Cn, eM CL, Cn, eM CL, en, eM CL, Cn, CH CL' CD, � CL, Cn, eM CL, en, eM CL, en, eM CL, en, eM cL, en, eM CL, en, eM CL, en, eM CL, Cn, eM CL, CD, � CL' CD, � CL' CD, eM

strips CL' CD, � strips CL, CD, � strips CL' CD, � 0.25 mil. CL, CD; clean/trip 0. 5 0 mil. CL' CD; clean/trip o. 75 mil. CL' CD; clean/trip 1.00 mil. CL, CD; clean/trip 0.25 mil. CL' CD; clean/trip 0.50 mil. CL' CD; clean/trip 0.75 mil. CL, CD; clean/trip 1.00 mil. CL' CD; clean/trip 0.25 mil. CL, CD; clean/trip 0.50 mil. CL' CD; clean/trip 0.75 mil. CL, Cn; clean/trip 1.00 mil. Cv CD; clean/trip

CL, Cn; AR effect CL, en; AR effect CL• Cn; AR effect CL, en; AR effect cL, en; AR effect CL, en; AR effect CL, Cn; AR effect CL, en; AR effect CL, Cn; AR effect CL, CD; AR effect

STR-25 5 9

Figure

2-1 2-2 2-3 2-4 2-5 A.1 A. 2 A.3 A.4 A.S A. 6 A. 7 A. 8 A. 9 A.10 A.ll A.12 A.13 A.14 A.15 A.16 A.17 A.18 A.19 A.20 A.21 A. 22 A. 23 A.24 A. 25 A.26 A.27 A. 28 A.29 A.30 A.31 A.32 A.33 A.34 A.35 A.36 A. 37 A.38 A.39 A. 40 A.41

s=�•�•� STR-25 5 9

Table 3-2 . Summary of Figures (Concluded)

Configuration Type Data Figure

NACA 4412, RN 0.75 mil. cL, CD; AR effect A.42 NACA 4412, RN 1. 00 mil. CL, cD; AR effect A.43 NACA 4409 , RN 0.25 mil. cL, cD; AR effect A.44 NACA 4409 , RN o. 50 mil. CL, cD; AR effect A.45 NACA 4409 , RN 0.75 mil. cL, CD; AR effect A.46 NACA 4409 , RN 1. 00 mil. CL, cD; AR effect A.47

AR oo, RN 0.25 mil. CL, cD; t/c effect A.48

AR "'• RN 0. 50 mil. CL, cD; t/c effect A.49 AR ro

, RN 0.75 mil. CL, CD; t/c effect A. 5 0

AR oo, RN 1.00 mil. CL, CD; t/c effect A. 5 1 AR 12, RN 0.25 mil. CL, CD; t/c effect A. 5 2 AR 12, RN 0.50 mil. CL, CD; t/c effect A. 5 3 AR 12' RN 0.75 mil. CL, cD; t/c effect A. 5 4 AR 12, RN 1.00 mil. CL, cD; t/c effect A. 5 5 AR 9 , RN 0.25 mil. CL, cD; t/c effect A. 5 6 AR 9 , RN 0.50 mil. CL, cD; t/c effect A. 5 7 AR = 9 , RN 0.75 mil. CL, CD; t/c effect A. 5 8 AR 9 , RN 1.00 mil. CL' CD; t/c effect A. 5 9 AR 6, RN 0.25 mil. CL, CD; t/c effect A.60 AR 6, RN 0.50 mil. CL' CD; t/c effect A.61 AR 6, RN 0.75 mil. CL, Cn; t/c effect A.62 AR 6, RN 1.00 mil. CL' CD; t/c effect A.63 NACA 4418 , AR 00 CD; wake rake B.1 NACA 4415 , AR 00 CD; wake rake B.2 NACA 4412, AR 00 CD; wake rake B.3 NACA 4409 , AR 00 CD; wake rake B.4

SECTION 4. 0

RESULTS AND DISCUSSION

The reduced data presented in Appendix A in Figures A.1 through A.63 are plots of lift coefficient, drag coefficient, and pitching moment coefficient versus angle of attack. In some of these figures, the full angle of attack range (-10° to 110°) is not presented. The angle of attack range was restricted to prevent the thinner blades from breaking, especially at combinations of high AR and high RN. The wake rake drag coefficients are given in Appendix B. Some of the important features of the force balance data are discussed below.

4.1 NACA 4418 SECTION (Figures A. 1 through A. 4)

Results of lift, drag, and pitching moment measurements are shown for blade aspect ratios ranging from co to 6. For each AR, results are shown for a Reynolds number range of 0.25 x 106 to 1.0 x 106•

For the two-dimensional case (AR = co), initial stall occurs at a = 18°. Since the blade was only supported at one end (Figure 2-2), a certain amount of bending and twisting occurred at high RN and high c1 conditions. Blade bending and twisting produce a somewhat finite wing, which affects the circulation around the wing and causes some loss of lift while increasing the drag. There has been no attempt to correct either CYi or the lift curve ax slope for this effect. Thus, as can be seen in gure A.1 (a), C Lmax decreases with increasing RN. For a true 2-D section the trend would have been reversed. The stalling angle of attack, however, is constant over the RN range. The (pre-stall) lift curve slope is more or less constant at o.og per degree over the RN range studied. This differs from the slope of 0.1 for RN of 3 to g x 106 given in Ref. 4. Beyond 18° the lift coefficient drops to a local minimum of o.g at 31° and then rises to a local maximum of 1.2 (secondary stall) at 42° before dropping off sharply with angle of attack beyond 46°. This 'double-humRed' lift curve occurs in all later plots. For RNs of 0 .75 x 106 and 1.0 x 10 6, the local minimum is 1.08 and occurs at 36°.

There is rapid rise in drag past CLmax [Figure A. 1 (b)]. Maximum Cn is reached at a = goo. This maximum value (2 .0 6) is close to the theoretical limit of 2. 0 for a two-dimensional flat plate at goo. The moment curves in Figure A.1 (c) show a somewhat stable characteristic up to a = 18 °, but a highly unstable characteristic at the higher angles of attack. A considerable amount of erratic change in pitching moment is noticed at low a ((100) for an RN = 0.25 x 10 6. This is primarily due to the lack of sensitivity of the moment balance at such a low dynamic pressure.

Similar trends are observed in Figures A.2, A.3, and A.4 for the finite blade with aspect ratios 12, g, and 6, respectively. An interesting trend is the decrease in lift curve slope and �max with decreasing AR. There is minimal change in the drag coefficient versus c1 curve, in going from an infinite AR to an AR of 12. However, for AR = g and AR = 6, the CD curve shows dramatic decreases at high lift coefficients. The effect of AR is discussed in detail later.

55�11.1 ----------------------.l.L!...!:�� '= �

4.2 NACA 4415 SECTION (Figures A.5 through A.8)

Lift, drag, and pitching moment curves for this section are shown for the RN and blade AR range mentioned for the previous section. For the infinite AR blade, c of roughly 1.4 occurs at a = 18°. A local minimum of 0.9 occurs

LmQx · o at 31°. secondary stall (c1 = 1.2) occurs at roughly 42 • As before, the C decreases with ascending RN in apparent contradiction to Ref. 4. The

Lmax 6 .

RN = 1.00 x 10 curve in Figure A.5 (a) shows premature stall. This apparent anomaly is yet to he explained. As for NACA 4418, the drag coefficient reaches a maximum at a = 90°. At high a, the airfoil behaves like a flat plate. The lift curve slope is 0.09 per degree compared with-0.1 in Ref. 4. The pitching moment is stable up to 10° angle of at tack. At high a, the pitching moment characteristic is highly unstable. As in the NACA 4418 case, erratic variation of � at RN = 0.25 x 106 [Figure 1.5 (c)] is observed.

Figures A. 6 , A.7, and A.8 show c1, C , and CM for aspect ratios of 12, 9, and 6. The same trends (secondary sta£1, shar1p increase in C beyond a tall, erratic eH variation with a at low RN, post-stall unstable cRaracterist�cs of eM , etc.) mentioned for the two-dimensional airfoil are followed in· these plots. The effect of aspect ratio on the aerodynamic coefficients is discussed later.

4.3 NACA 4412 SECTION (Figures A.9 through A.l2)

A c1 of about 1.35 occurs at an angle of attack of 17°. The pre-stall lift curv�a�lope is 0.09 compared with the value 0.1 given in Ref. 4. The local minimum (0.9) is the same as that for NAeA 4418 and NAeA 4415. However, it occurs at a lower (26°) angle of attack. Secondary stall (e1 = 1.2) is at roughly 44°. eDmax (2.06) is at 90° and the low RN eM is somewhat erratic.

4.4 NACA 440 9 SECTION (Figures A.l3 through A.l6)

Initial stall occurs at 15 ° and the local minimum (0.92) is at 25 °. The lift curve slope is 0.1 per degree. The drag and pitching moment curves follow the same previously mentioned patterns.

4.5 NACA 4415 SECTION WITH BOUNDARY LAYER TRIPPING (Figures A.l7 through A .31)

The aerodynamic characteristics of the NAeA 4415 airfoil with boundary layer tripping are presented (Figures A.17, A.l8, and A.19) along with a comparison with the clean airfoil (Figures A. 20 through A. 31). The trip strips are described in Section 2.0. Three aspect ratios ( oo, 12, and 6) were investigated at the four Reynolds numbers.

The lift curve slope for the airfoil is roughly 0.086 per degree. The eLmax is found to decrease (and occur at progressively lower angles of attack) with increase in Reynolds number. However, in all cases the post-stall local

s=�� '*' ________________________ ___::S� T.::.R-�2::..:5�5:.::_9 - .§��

minimum (0.92) occurs at a = 310. Secondary stall occurs between 400 and 45°. C

D reaches a maximum ( 2.12) at a = 90°· The pitching moment shows a stable condition at pre-stall angles and shows highly unstable characteristics at high angles of attack.

For the two-dimensional blade at low RN (Figure A.20), the boundary layer trip decreases the lift curve slope, lowers C , and generally lowers the lift curve for angles of attack up to the locatm�lnima. These minima ( 0. 9 at 31 O) and the lift curve beyond this point are the same as that for the clean airfoil. The decrease in the lift curve slope is more pronounced at higher RN ( Figures A.21 through A.31). The same trends are observed for the blades with aspect ratios of 12 and 6.

As can be seen in the figures, the drag coefficient is not much affected by the trip strips except at lmv- aspect ratios. The effect on pitching moment is not presented hut may be in f e rred from Figures A.5 through A.9 and A. 17 through A. 19.

4.6 EFFECT OF ASPECT RATIO (Figures A.32 through A. 47) In these figures the effect of aspect ratio variation on the aerodynamic characteristics (specifically lift and drag coefficients) is presented for the 1 6 different airfoil section-RN combinations. For example, Figure A.32 shows c1 and CD f or NACA 441 8 with AR of "', 1 2, 9, and 6 at RN = 0.25 x 1 06. A general lowering of the lift coefficient curve over the angle of attack range - 1 0° to 90° is observed to occur with decrease in aspect ratio. An interesting consequence of the AR effect is that in some cases [for example, in Figure A. 32 (a) for ARs of 9 and 6] the second local maximum (secondary stall) completely disappears, and the lift falls off continuously from a maximum at initial stall.

The drag coefficient is significantly reduced with a decrease in aspect ratio at post-stall angles of attack. Figure A.32 ( b) is a typical representative of this effect. In this figure, CDmax

has a value of 2.06 for an AR of oo, but i's L 32 for an AR of 6. Both maxima occur at 90°. These trends may be compared with those given in Ref. 5 for low aspect ratio wings with Clark Y airfoil sections at RN of 0.153 x 106• The lift and drag coefficient curves in Re f . 5 are qualitatively similar to those in this report. In particular, the CD in both cases occurs at 90° and its value falls in the 1.2 to 1.6

max range.

4. 7 EFFECT OF AIRFOIL THICKNESS (Figures A.48 through A.63)

The airfoil thickness affects c1 and a l. • This is true for the entire

. ,l)lax sta 1· RN range stud1ed. CLmax

and astall both decrease with decrease in th ickness. Although the local minimum lift coef ficient is the same for all four thicknesses, the angle of attack at which this occurs decreases with decreasing thickness. In general the post-stall drag coefficient increases with decreasing airfoil thickness. This again is true over the entire RN range studied.

s=�� ·• -----------------------=S T=R'"'----'=-2""-5 )�r9

SECTION 5.0

CONCLUSIONS

Force and moment data are presented for nonrotating NACA 4418, 4415, 4412, and 4409 wind turbine blades with aspect ratios of infinity, 12, 9, and 6 for Reynolds numbers of 0.25 x 106, 0.50 x 106, 0.75 x 106, and 1.00 x 106. From these data the following conclusions are observed:

• In general, the lift coefficient data showed both initial and secondary stall over the angle of attack range of -100 to uoo. The maximum drag coefficient occurs at 900, with the highest value at 2.1 for an infinite aspect ratio blade. The pitching moment is unstable beyond stall.

• The lift coefficient decreases with decreasing aspect ratio. For aspect ratios of 9 and 6, secondary stall is eliminated. The post-stall drag coefficient decreases significantly with a decrease in aspect ratio.

• The lift coefficient and stall angle of decreasing airfoil thickness ratio. , The increases with a decrease in thickness.

attack both decrease with post-stall drag coefficient

• In the post-stall region, the lift and drag coefficient were relatively insensitive to Reynolds number effects over the range tested. The unexpected increase in maximum lift coefficient with decreasing Reynolds number is attributed to blade bending as a result of the higher dynamic pressure.

• Boundary layer tripping is observed to decrease the lift curve slope, the maximum lift coefficient, and the stall angle of attack. The drag coefficient is sfgnificantly affected only at low aspect ratio.

SECTION 6.0

REFERENCES

1. Pope, A. and Harper, J. J., Low-Speed Wind Tunnel Testing, John Wiley & Sons, New York, 1966.

2. Mechtley, E. A�, International S stem of Units - Physical Constants and Conversion Factors NASA SP-7012, 1969.

3. Low Speed Wind Tunnel Facility Handbook, Aerospace Engineering Division, Texas Engineering Experiment Station, The Texas A&M University System, College Station, Texas, January, 1982.

4. Abbott, I. H. and Von Doenhoff, A. E., Theory of Hing Sections, Dover Publications, Inc., New York, 1959, pp. 488-493.

5. Knight, M. and Wenzinger, C. J., Wind Tunnel Tests on a Series of Hing Models thorugh a Large Angle of Attack R ange, P art I - Force Tests, NACA TR 317, 1929.

STR-2559

APPENDIX A

FORCE AND MOMENT DATA

This Appendix contains Figures A.l through A. 63. The figures are summarized in Table_ 3-2.

1-z w H

u H [l_ [L w 0 u

1-[L H ..J

2 . 0 0-.----------� l---------1

1.60+---

1.20+----

I . I ----+-·----------�----------1

I -- ---�---�

-r------1-------�----+-----m----- -+------+-1 _j _____ -

. I I I Symbot RN (x io6)

8 0.25 1

0 0 . 50

&. 0.75

'\[! 1 . 00

------r --------';--1

- 0 .80+---�---+----r---+----r---4----.---�-------4----.-� -10.0 0 1 0. 0 0 3 0. 0 0 5 0 . 0 0

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90.00 1 1 0.0 0

Fi gure A .l - f\�r.:Qdynami c Coeffi c ien ts of the NACA 4418 Ai rfoi l , AR = oo.

I--z w H u H lL lL w 0 u

(.!) <( cr 0

2 . 8 0.------, ,--1 . I 2 . 40+--------------�----J___ -+-_ ------ 1--------

1 1 I ·

• I I I r , I ' I I ! Symbo 1 RN ( x 106) l I ----m-, --R

2. 00+--------t-

0 0.25 r----------l-·-:::::- ------r-----".� I) 0 0. 50 I /' I

8 o. 75 I // i i · 9 1 oo � P I ! : t • ; II 1 i \

+-------+- ----- �-------�-- -- --------;---------------- ----r·-- ---- - --------� ' . I I I I I i ' ! I I I

I ! I 1-� --r-------+------t---------------ff-1-) _J ___ __L_

I I . . I I I o. 80-r------------1 �---1- I

+ . I 0 . 4 0+------- ----!--l1h-- --j-----

0.0��--�--��--�-�--�--�--�� - 10.00 10.00 30.00 50.00

ANGLE OF ATTACK

( b ) Dra g

(DEGREES)

Figure A.l- Contin ued .

90.00 1 10.00

I -0. 60+----------j---- -------------t·----i

-0.70+--�-�--�---4----�--4---�---+--�----�---�--� -10.00 10.00 30.00 50.00

A NGLE OF A TT ACK

(c) Pitch i n g Moment

Fi gure A.l- Con c l uded o

(DEGREES)

90.00 110.00

1-z w H t.l H lL lL w 0 t.l

1-lL H _J

2 . 0 0 -.--------,-- r--�---� 1 . 60+-----+----+--

-___ 1 symbol RN (x io6) +---------�

0 . 8 0

0 . 4 0 !

0 0 . 25

0 0 . 50

8 o. 7 5

1 . 00

-0.80+---�--+----�-+---�--4---�-4---�---4----�-� - 1 0 . 0 0 1 0.00 3 0.0 0 5 0 . 0 0

ANGLE OF A TTACK

( a ) L i ft

7 0.0 0

(DEGREES)

9 0. 0 0 1 1 0. 0 0

Fi gure A.2 1- Aerodynami c Coeffi c i ents o f t h e NACA 441 8 A i rfo i l , AR = 12 .

2 · BO.......----l --�--r ,-------r---------l I I I I I I I I I I I I I I 2. 40+---- --------+1--�-1------+ ---! --� : I I I ' i I ! I Symbo l RN ( x 106) / i I

2 .00+---�---+-------- : �� L _____ + li & 0.75

I \'l 1. 00

� 1 . 80+----+ --·-1-------t H

LL LL w 0 u

� 1 . 20+-----+--

I 0. 40 ___ ----r·--0 . 001��--�--�--�--�--�--��--�--�

- 1 0.00 1 0 . 00 30 . 00 50 . 00

ANGLE OF A T T ACK

(b) Drag

70 . 00

(DEGREES)

Fi gure A. 2 - Continued .

90.00 1 10 . 00

0. 00 ...----· r---,------,-------- � - --r-----� I I I I • I

�-�� I -5 ' \ � 1 ' · � . ; Symbol RN (x 10 : -[--------0<,� T---------- ---G 0. 25 -------------

\� 0 Oo50 ! \ 8 0.75

'\f) 1. 00 . I- -0. 20+--z

--N'"=--·--r-----------:--�-------t-----� t ' I : l l ! ! w H u H !L. LL

U.J --n SO+--o ....; .. ... l � I z l w ! � I

·��\. I '

�� ,, '\ . -- ---- ---· · - ---+·------- -, - - ......... , . ---i � l t '<" I '" ! � -0. 40+-------+------� ------L----1---� --+-------1 I . I!J

I u Il-l

! I 0.. -0. 50+----·-�- -+----+-� I I

1 � ! I i I I -0 . 60-+-----t-----r------�-------------:j--·-·- -----

1 ! ! i

-0.70+--�-�---�--�--��-+---�---4�--�--�--�--__, -10.00 10.00 30.00 50.00

ANGl_E OF ATTACK

( c ) Pi tchi ng Moment

Figure A. 2 - Cone 1 uded.

(DEGREES) 90.00 110.00

1-z w H u H lL lL w 0 u

1-lL H . _j

2. 00.........-------·-1------.--T---- --T·-··-····----r ��-l----�-l i I ! l 'I I 1. 60-+--------i------r--------r-------- ! -------1 ,

• -6 I \ I Symbol RN ( x 10 ) \ I : 8 0 .25 . I I '

1 . 20+------t-- -l 0 0 .50

0 . 80

I 6 I 0 .75 I I

I I I I -t-

I t-I I

I I I _J_ I I I I I I I

1 I · t-- ·:--t-I

0. 0 0+----��------1' ·-t---�---r------r- ---� I I ! I I I i i I I I ---�·----+' ---+- --- -- t - - -- r-

-0 . 80+---.---�---.---+---.----�------+---�--�--�--� - 10 . 00 1 0 . 00 30 . 0 0 50 . 00

ANGLE OF ATTACK

( a ) Lift

70 . 00

(DEGREES)

90.00 1 1 0 . 00

Figure A . 3- Aerodynamic Coefficients of the NACA 4418 Airfoil , AR = 9.

r-z w H u H LL LL w 0 u

(!) <t II 0

2. so�T�---1---------T--� T��-1- � �--1 I I I I ' i i i I ! ! I --i- ! I

2. 40+-------r--1 -- � -----r·------, l ! I I ! i I I I I 1 I '

2 OO+-------+' ______ j ______ t Symbol RN (x 106) r-' ___ j_ • I (!] o.2s !

! ' ' i

1 . 80

1 .2 0

i o o. so 1 , I A o. 75 I I -1-----+ -1----�-r--�- r

1.00 1 _

__ -----l : I I I l I ,' I I II I i j I, I ! I , : I I !

---�----��---

I I I ! I I I i 0 . 8 0+-----t--t-- t----��---��

I I I I

0.4 0+---�-+--- ---- +� I - --+- I I : I I

0.001�--��r---��---J--�---t--�--�--�� - 1 0.0 0 1 0.0 0 - 3 0.0 0 5 0. 0 0

ANGLE OF ATTACK

( b ) Drag

7 0. 0 0

(DEGREES)

Figure A . 'J - Contin ued .

9 0 . 0 0 1 1 0 .0 0

--0 . 20+---------+--r--z w H u H

0 . 50 0 . 75 1. 00

i I I I �------------, . I I : I : I I i ! I ------!--·-----�- ------�J

�· I I I ! - 0 . 4 0 ��·-��1 �I ��

3 I I � I I � - 0 . 5 0 +---------+--------+-------�--------+-------�------�

-0 . 60+----

-0. 7 0+---�---+--��--+---�---+----�--+---�--�----�� - 10 . 0 0 1 0 . 00 30.00 50 . 00

A NGLE OF ATTACK

( c ) P i tch i n g Momen t

Fi gure A . 3 - Conc l uded o

7 0 . 0 0

(DEGREES)

9 0.00 1 10.00

I-z w H (J H LL LL w 0 (J

1-LL H _I

2 . 0 0.--------.---------�-------.--------, -------�----

1 . 60+-----�-+--------+--------+�------+---------+------�

Symbo l RN (x 106) 1 . 20 G 0 .25

0 0. 50 8 0 . 75 '\'} 1 . 00

0 . 80

0 . 40 --�-t

-0 . 80+---.---�---.--��--.---1----r---+---.,---+---�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

Fi g ure A. 41- Aerodynam i c Coeffi c i ents of the NACA 4418 Ai rfo i l , AR = 6-.

2 . 8 0-r----1____ __ �----T 2 . 4 0+-------t- ------ -- - ---- - �----- ----- --l--------

11 I I I i I I I I J I

2 • 0 0+------ -1- ------l _sy_m:-. o_l --��-2-� x_l0--=-6 ) �--- ----r--�

! l 0 0 .50 I ! I

� I I 6 0 . 75 I I i � 1 60+-----�'-- I \l 1. 00 �- I ---� u · 1 --f 1 1 1 H 1 1 1 r 1 lL t \ lL l i I I g I I I I

: ! I � 1 . 2 0 -t-------t·--- -- - ----l--, -----...11�-

§ i I I I I I 1 I I I I I ' I : 0 . 80 -+-----------1-

-+---------,,o;L-+----t-----t ---� 1 I -t' - : 0 . 4 0+---- --+----HJ---- -- ------}--

1 0 . 0 0 3 0 . 0 0

1 I I I 5 0 . 0 0 7 0 . 0 0 8 0 . 0 0 1 1 0 . 0 0

ANGLE OF ATTACK (DEGREES)

( b ) Drag

Fi gure A . IJ - Conti nued .

Q . QQ...-----1- -Q . 2Q+----· z w H u H lt Symbol RN (x 166) � -Q • 3 Q +---- I --""'...,....W.-----'-U 0 0 . 25 I � : �: �� I I � -Q . 4Q+-----! 'Yj 1 . 00 �------�--� I z H I

� - 0 . 5 0 +------+-- --+------+-,---------l--1 -�· ! I I

! I [ I 1 -Q . 6Q+-----·-r

,' · - --·----+-----·--·-�! ---·-----�------··-i-------

t I I I 1 I I -Q . 7Q+--�--�--�---+--�--��--�-+---�--�--�-� - 1 Q . QQ 1 Q . Q Q 3Q . Q Q 5Q . QQ

ANGLE OF ATTACK

( c ) Pitching Moment

Fig ure A . 4 - Con cl u ded .

7Q . QQ (DEGREES)

8 0 . 0 0 1 1 0 . 0 0

}-z w H u-H

lL lL w 0 0

}-lL H

2 · O O -r------ r----T--,----�r---1---l I I I I j j i Symbo l RN ( x 106 ) 1

1 . 80+----------�'--·- ----1

-----+ 0 0 . 25 _ ___ _j . I I I I I 0 0 . 50 I I /'.. I - I (..!.) 0 . 75 I I !

1 . 20+------

l --:--�1 . 00 �-� 0 . 80

0 . 40

l9\ l ' i ' I I ,· I I , \ I 1 I : r ! \ I I : I ! ! \ I I 1

_______ j l--- ----- - -----� -- - --- - -- -- --- --T -- - - --- ---',�- ---- ---- ·-l1------ - ------� ! / 1 \ I ! i \ I l

+-----1 -- __ , _j_ _ _ L ------f· .. __ \, _ __j __ __ _J_ lj I ! i I I

' I I I I \ l I 0 . 00-+---�----+--- -- -·r------1-------1- - -1\--_J,,

i I I I i \ ! I I I \ I �---- t-------- ·-- --t ------- ---r-- - - - -4------ I -�

I I I I I \ l I ! I I \ j I I ' '

-0 . 80+---.---�---.---+---.-----�------+---.---�--�--� - 10 . 00 10 . 00 30.00 5 0 . 00

ANGLE O F ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

F i qure A . S - Aerodynami c Coeffi ci ents of the NACA 4415 A i rfo i l , AR = CG .

1-z w H u H LL LL w 0 u

(.!) <! a: 0

2 . 80 -r-------·--�- ----r------ ______ _ 1 _ __ _ _ _ _ _ __ 1 ___ _ l i I I l I

2 . 4 0+----------�--- : - __________ j ______ �-�--� I I ! I I I - 6 I I I

, symbol RN ( x 10 ) j j

2 . 0 0+---- : �:�� -- - -- - Yc�a-_-_-t._ r----e_�-. --.d!

1 . 80

1 . 20

\:1 1 . DO / I I · ;( I I +----- ---- --+ -- _____ __ ___ _ J_ __ --�---+--

I / I I ! 1

+---- _ I ----+---17.-t-----+--------_j-----1 I I I

0 . 80 �-------r-------+�t----�------+------- -----�

0 . 4 0+----

I I I ---i--

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Drag

Fi gure A. 5 - Conti nued .

7 0 . 00

(DEGREES)

-- --! 9 0 . 0 0 1 1 0 . 0 0

Symbo l 0 . 25

I I I I o n. so 1 ·� � - 0 . 20 ---· : �: �� -· I � - o . a o I --- J _ _ __ _ J � � I I I I

z I · I � I J ! I '\ I I I �f::� - o . 4 0L__11' -- -�----�- --�L----t- !

I l I I H ' : i I I I I \ I o.. - o . 50 I ------t------ I ---- ----�--

j I I' I I I I I I I I i i I i � ' I -0 . 60+------ 1------+------+ - ------t-----i-�

I i I I I I -0 . 7 0+---�--4---�--�--�---+--�---4--�--��--��

- 1 0 . 0 0 1 0 . 0 0 30 . 0 0 50 . 0 0 ANGLE OF ATTACK

( c ) Pi tch i n g Moment

Fi gure A. 5 - Concl uded o

70 . 0 0 (DEGREES)

90 . 0 0 1 1 0 . 0 0

2 . 0 0 -r--------T------ _________ ___ _

I I --·l

Symbol 8

0 .25 0 . 50 0 . 75 1 . 00

I i 0 . BOj -i CJ

t 0 . 4 0+----tlll�-+----· ----1 H _J

O . OOr--7�--�------�!--------�----- -----1--------i

I I I + I I I - - · ··-- ---- --1"--- ------� -----�------ -----r-

-O . BOr---.---,_---,--+---.----r---.---+---,---�--�--� - 1 0 . 0 0 1 0 . 00 3 0 . 0 0 5 0 . 0 0 7 0 . 00 9 0 . 0 0 1 1 0 � 0 0 ANGLE OF A TTACK WEGREES)

( a ) L i ft

Fi gure A .6: - Aerodynami c Coeffi ci ents of the NACA 4415 Ai rfoi l , AR = 12 o

1--z w H u H lL lL w 0 u

C!l <! cr 0

8 0..------ --r---- r ----r -- -- - -----r-1 I I I I I I I !

2 • 4 0 +---- -·-·-- -l--·--·--·- · --- -·t·---------�' --·· -----·---- ·-··-- ·-----t--- I I i II I I I . 2 . 0 0 +---

1 . 80

Symbo l 0

I I I 6 0 . 75 --t----- r---- -- _ _ , _ "' - r_:_._'l_D_ _ _ T ___ - ··-� I I ·

1 . 2 0

I I I +----- --1 ------·---�-------+- I. � - -- - - --�-------!

I I I I I I

0 . 8 0+----

I _ I I

0 . 4 0 +-----+-�- ,

__ - ____ J_ _ _ __ ------r--� 1 0 . 00 30 . 0 0 50 . 0 0

ANGLE OF ATTACK

( b ) Drag

Fi gure A. 6 - Conti nued .

7 0 . 0 0 (DEGREES)

90 . 0 0 1 1 0 . 0 0

0 . 0 0=------l------

-- r---l------· --ll ___ _ l -o . 1 oil��llll+r-+l _________

sym:o l ��2�x Jii6 J 1 - -� 0 0 . 50 II I 8 o . 75 I '\;} 1.00 I I

1-- -0 . 2 0+--- -+--------i aJ · 1 I H u H I.L I.L gj -0 . 30+--CJ

f-- I aJ I 1 � I ' -� -0 . 4 0-+---------+----------r----·- --- -i -t------ -f··-·----� I . I � I '

I I 1-- I I I I � -0 � 50 -T------t ---r-· ·-----r -t

I I I ! I I I I I i -0 . 6 0+---- ----t- - -----1--- -- ---t --- ----t- -- -- �-��

l I I I I

- 0 . 7 0+---�--�--�--�--�--��--�--�--�---4 - 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTACK

( c ) P i tch i ng Moment

Fi gure A . 6 - Conc l uded .

7 0 . 00 (DEGREES)

90 . 0 0 1 1 0 . 00

f-z w H (..) H l.L l.L w 0 (..) f-l.L H _J

2 . 0 0..--------.-

1 . 80 -r Symbo l RN ( x io6 ) 13 0 . 25

1 . 20 0 0 . 50 -- 8 0 . 75 '\(! 1 . 00

0 . 8 0

I � I I 0 . 4 0 ---1-- --

I I I 0 . 0 0

l ---r--- ----I

-0 . 4 0

j_ l -+--� I - 0 . 8 0+--.---+--.---�-.--�-�-�--�--�--�-� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 0 0 1 1 0 . 0 0

Fi g u re A . 7 - Aerodynam i c Coeffi c i ents of the NACA 4415 Ai rfo i l , AR = 9 .

2 . 80�--r- --r ---- __ J _ _ _ _ l 2 . 4 0+-----t-------+---+--� I i 2 . 0 0+-------+' ----1------

� I Sym�o l

��2�x 166 )

w 0 0 . 50 1' 8 1 . 80+------+------l 6 0 . 75 ,--------! � I "' 1 . 00 I

u I I � 1 . 20+-------4------�------+--��------� 0 . 80�------+ ----�·

------t------- ---- -- --------+-------;

o . oot}-.��---t--�--J---�--t---�-J--�--� - 1 0 . 0 0 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 7 - Conti nued o

70 . 0 0 (DEGREES)

90 . 0 0 1 1 0 . 00

o . o��------.----------.--------.--------.---------r-------�

Symbo l 0 0

0 . 25

o . 5o I 0 . 75 �I 1 . 00

� -0 . 20+-------�---------+------��--------�------- , � I H u H LL LL � - 0 . 30+-------�--------�-- -----�--------+--------4--------� u

1-z w � 0 i - 0 . 4 0+--------+-----�--�� --t--------- r I u 1- I

� -0 . 50+-1 ----+-------+

-0 . 60+-----+-----+---+----+--

-0 . 70+----r--�----�--�--�----+---�--��--�--�--�----4 - 1 0 . 0 0 1 0 . 00 3 0 . 0 0 50 . 0 0

ANGLE OF ATTACK

( c ) Pi tchi n g Moment

Fi gure A. 7 - Conc l u ded . 4 1

7 0 . 00 (DEGREES)

90 . 00 1 1 0 . 00

1-lL H _J

2 . 00 -- --- --l-1 . 60 -i --+

I I I Symbo l RN ( x 106 ) I

-------� 0 0 . 25 !-�� 1 . 20 0 0 . 50 I 8 0 . 75 I 'VI 1 . 00

0 . 80

0 . 40

0 . 00 �-+----l------�·-1 ---t---

-0 . 80+---.----+----.---+----.--�----.---4----.---4----r---� - 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0 (DEGREES)

90 . 00 1 1 0 . 00

Fi g u re A . 8 - Aerodynami c Coeffi c i ents of the NACA 441 5 A i rfo i l , AR = 6 .

2 . 8 0 �------�------ r- . 2 . 4 0+-----+1----+----�-----+------+----_j

II i I i I , I l I

2 . 0 0+---- ----t--11 __ -r----t-----i-1 i I I i i I I I r- +- ,, I � 1 . s o+---- ---r-------f _sy_mEJ_�o_l __ �-� 2-�-x _1_66_) �--

H ! I I lL I 0 0 . 50 I � ,1, i 8 a. 75 I u i I 'V 1 . oo I � 1 . 20 -----· · rr i �� o I !

0 . 80+-------+------1--�+-------+-----h I

0 . 0 0��---J--�---t--�--�--�--�--�� - 1 0 . 0 0 1 0 . 0 0 30 . 0 0 50 . 00

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 8 - Conti n ue d .

7 0 . 0 0 (DEGREES)

90 . 0 0 1 1 0 . 0 0

I ---l I .

�;�'r\ 1 I- -0 . 2 0 +-------'lt--i \

---+-- I

I I I w � -0 . 30 _ I j a s I __ _ t·� Symbol RN ( x 106 ) 1 u

1-z w ::::E: 0 ::::E: -0 . 40+--------+--------+-------t!l z H I u 1-H

[:! 0 . 25

o o . 5o : 1 A 0 . 7 5 ----l \'1 1 . 00 I

a.. -0 . 50+--------+-----+-----+-------t------t-- --�

-0 . 60+------� ----�--------+--------+------- ·1-------4

-0 . 70+---�--+--�r---+---�---+----r---�-----�----� - 1 0 . 00 1 0 . 0 0 3 0 . 0 0 5 0 . 00

ANGLE O F ATTACK

F i gure A . B - Conc l uded .

7 0 . 00 (DEGREES)

90 . 0 0 1 1 0 . 00

f-z w H u H LL LL w 0 u

f-LL H _J

2 . OO--r----1 ____ T __ _ _

Symbo l RN ( x 106 ) 1 . 80

I I ------�- ·----

0 . 80

0 . 40

0 0 . 25 0 0 . 50 6 0 . 75 \:1 1 . 00

---- --

---T- +-�� I I \ I ·---+--\\----1-

·-t-----l---+----.J-.l.., II \. \

t--- \

30 . 0 0 -0 . 80��.-��---.---+---.--��--.---+---.---�--�--�

- 1 0 . 00 1 0 . 0 0 1 1 0 . 0 0 50 . 0 0 7 0 . 00 (DEGREES)

90 . 0 0 ANGLE OF ATTACK

( a ) L i ft

Fi gure 1\ , 9 - Aerodynami c Coeffi c i ents of the NACA 441 2 Ai rfo i l , AR = co

2 . s o��l �� -

2 . 4 0+----+-t �--�--+1 I

2 . 0 0+---Symbol

0 . 25

0 . 50 � --f-- 6 o . 7 5 I /-/ Gj v 1 . oo I � 1. 60 +----·---�- --�-------+

/--; ---+-------+-,-----1

� 1 . 2 0+-----f-cr: 0

0 . 8 0+-----+------+--- R-------t----·-- ------1----�

I 0 . 4 0+-----·�----flt"-·-t------t -- -+-----l-----l

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Dra g

Fi gure A . 9 - Conti n ued .

7 0 . 00

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

Symbo l RN ( x 166 ) f-.

- 0 . 20+-----+--z w H u H lL lL

8 0 1!:::. "' � - 0 . 30 +-------+---------+---��-+----

f-. z w L 0

� -0 . 40+-------+-------+--------+--�---� (.!) z H I u f-. H

a. - o . 5 0+---------+·-----+---

-0 . 80+-------4---

' 0 . 25 --� 0 . 50

0 . 75

1 . 00 I , ----i

-0 . 70+--�--+-�----+---�---+--�r---+----r---+---.----; - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 0 0

ANGLE OF ATTACK

( c ) P i tch i n g Moment

7 0 . 0 0

(DEGREES)

Fi g ure A . 9� Concl uded .

9 0 . 0 0 1 1 0 . 0 0

1-lL H _j

2 . 00 ---- -- I j ___ + I i

1 . 60 I I �- ·------

I Symbo l RN ( x io6 ) (J 0 . 25 I 0 0 . 50 ! 1 . 20 D. 0 . 75

VJ 1 . 00 I I I �� --� 0 . 8 0 I

---r---· I I i�_ I '

I I I I

0 . 4 0 �-----·, \ I \ \ I I

0 . 00 I -----r- I I I I I \ I I I I - 0 . 4 ---t----t- � - 0 . 8 0+---.----r---.---+---.----�--.---4---�--�--�--�

- 1 0 . 0 0 1 0 . 00 3 0 . 0 0 5 0 . 0 0

ANGLE O F A TTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 0 0 1 1 0 . 0 0

Fi g ure A . 1 0 - Aerodynami c Coeffi ci ents of the NACA 4412 Ai rfoi l , AR = 1 2 .

!-z w H u H lL lL w 0 u

(.!) <{ 0: 0

------- ---------� -�-----

2 . 4 0+------+-

2 . 00

1 . 80

1 . 20

t-- Symbo l RN ( x 106 ) r.::J 0 . 25 ' 0 0 . 50 I . I 6 0 . 75 \7 1 . 00 f--·--t-

I I I I +---I

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Drag

Fi g ure A . lO� Conti n ued .

70 . 00

(DEGREES)

9 0 . 00 1 1 0 . 0 0

0 . 25

l i 0 . 50

0 . 75

1 . 00 l r0 - 20 , l-l j � .oo�---�--��--��-� !- I t � \ I . L I \ I I I � -0 . 40 + 'k ·i--� z j . I ' ' H \ � I I o_ -0 . 50+----1-------+·--�---- I -r-

1 I l1 J1 l I I !

-0 . 60+----+- __ ___ r-------�-----··----,----l -0 . 70�--�--�--�--�--�---+--�---4--�--�r---��

- 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF A TTACK

Fi gure A . lO- Conc l uded .

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

1-LL H _j

2 . 00...-----l-----r�--, r _ _____ l _ _____ l ' I I I

I i I I I 1 . 60+-------+------+-----+---+--- �� 1 I Symbo l RN ( x 166 ) I 1 . 20+------+

___,IKIJ! --- : � : !� II 8 0 . 75 1 '

0 . 80

0 . 40

VJ 1 . oo I ·--- --+--

I I --1 I I

---l ---� I ----r---

-0 . 80+---�--4---�--�--�--�--�---+--�--�--�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF A TT A C,K

( a ) L i ft

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

Fi gu re A . l l- Aerodynami c Coeffi c i ents of the NACA 441 2 Ai rfo i l , AR = 9 .

l!l <! cr: D

2 . 8 0--lr ,---- -II

2 . 4 0 �-- ---+1------+1 -

----+! -+------1 J _J I l

-6 I j Symbol RN ( x 10 ) I

2 . 0 0 +------+�

----+ 8 0 . 25 I t---- : I 'I 1 ,. 0 o . so I I I I I I A 0 . 75 ! I

1 . 80

1 . 2 0

i I I !

I ' I I �--�--�---� I I I I I I I 0 . 8 0 -1-------+------+----/-A(Jl- r-- �-1-��

l i I 0 . 4 0+----

I 0 . 0 0��.-��--�--�--�--�--�--4---�--�--��

9 0 . 0 0 1 1 0 . 0 0 - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE O F A T T A CK

( b ) Drag

Fi gure A . l l- Cont i nue d .

7 0 . 0 0

(DEGREES)

0 · O O'Ttr--- -l------r- _ _ _ __ T ____ l ____ l __

I I Symbo l RN ( x 166 ) I -0 . 10

I I I I r- -0 . 20 --t-------I z I w I

H I u H , LL I I LL I gj -0 . 30 -+--�-- I u

I t j I I I I r- I z I w , ' L I I I 0 __j_ I L -0 . 40 f I t!l I z t H I u I r-H a. -0 . 50

-0 . 60

----- 0 0 . 25 . +------!

0 0 . 50 !:::. 0 . 7 5 '\! 1 . 00

-r - ----- 1

I I I -----! --r I I 1 ' I I I I I -r--I I I I -� I I ' I l +-

-0 . 70+---�--�--�---+--�----�--�--+---�--�------� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

F i gure A . l l- Concl uded .

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

1-lL H _J

2 . 00�---�,-

- --�--l -- -r--- r--1 I I i I I 1 . 80+-------+-------

I; �- ----i----- i l

' I I 1 I Symbo l RN ( x io6 ) ; l . 1 El o . 25 I �

1 . 20+-----1----- ---�--- r r 1 o o . 5o 1 ---1!1 I e:. o . 75 �� 1

0 . 80

0 . 40

\:7 1. 00 ' l t----f!--��-+-----J I

i I I I

l : ! I +---w---i ----+-------+-------1��-+�

i I I I

I I 0 . 00+-------fi--+----f---t---- -

I I I ' l I i I ,�-------+--------t------ --1------------- 1 _______ _

-0 . 80+---.---+---�--+---�--+---�--4---�--4---�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

Fi gure A . 1 2- Aerodynami c Coe ffi c i ents of the NACA 4412 Ai rfo i l , AR = 6 .

2 . 80�

� I I

2 . 40+--------+i--------r-----l---2 . 00+-----+--------

I I Symbol RN ( x 106 ) l I

--8-· --0-.-2-5 -- :----t--0 0 . 50 ' i

i-- 6 0 . 7 5 i

l ! z I w \-} 1 . 00 . � 1 . 6 0 I - T- ------t-----1 � I I i 1 . 20+-----+------+----- -+'----7----r--/ +i ----- j-� 0

I I 0 . 80+--- I ' i I

I :l _______ t __ ____ ·

I I I � r 1

0 . 40+----f-- ----,�---t----t------i---------i

0 . 00��--��--�---L--�--�--�--�--�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

( b ) Drag

Fi g ure A . l 2- Cont i nued o

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

�----r---1--- -.. - ---1-.-·----0 . 1 0

f- -0 . 20+-----+---z I w H I U I H I tt j ---'Sy'--m_bo_l

___ �----..:. � -0 . 30-+-------j [:I

� li 0 z 8. � i

0 . 25

0 . 50

0 . 75

1 . 00 0 I � -0 . 40+----+------.......--t!) z H :c u f-H

------, ! l I I I I I -� I 1

"--- "", � ----l I I I_ I I

I � -0 . 50+-------�-------r-------+------�

-0 . 60+-------+

-0 . 70+---��--��--�---+--�--�--�--�r---�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

( c ) Pi tchi ng Moment

Fi g ureA . l2- Concl uded .

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

1-lL H _j

2 . o o �- -----T-- ---- --- - -T-- ----- - - - -�-- -"-- - - - - - - -�---- - - -- - - - -- -- � -- -- -- ----l I I i ! I i I \ : . I ! i ! Symbo l RN ( x 106 ) i

1 . 80+-------- ---t-- ·-------+ -- -- -------- +- 8 o . 25 �-----i ) i ; 0 0 . 50 i !

1 . 20+---

0 . 80

I ! 8 1 : I i 0 . 75 . ! _______ __ J_____ 1-�- - -� I I

l�--1 . I I I I I I I I

I I I I I I I : i I -- - - - - · ------·i----------1

: I i I I

0 . 40 ! i J i +----'!M---_J·-----·---+-·-- -- ,---·-··--·i--1 I I I

I : ----+-- -----4

I I I ! ! I i I ! ' I I ! I 0 . 00+----lf-- ·-+-- +----i----------t--·-· -----�

I I I I I ' ,

i I I I ·--+--- t- ---- -------4-----''r---1 '

-0 . 80�--�---+---,r---+---�---+---,r---+---�---+----r--� - 10 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

Fi gure A . l3- Ae rodynami c Coe ffi ci ents of the NACA 4409 Ai rfoi l , AR = co • '

2 . 8 0-.------ --- _______ T ____ T ________ -------� l 2 . 4 0+----

2 . 0 0 +---

� 1 . 6 0 +-----+--�- ��-t�-------+--___, It I I I l I : 1 . 20 1 Symbo 1 1 RN ( x 166) �-----1 gj El o . 25 1

0 . 8 0-+--------l

0 0 . 50 /:!:. 0 . 75 -,--

I I ' I I I ! . 0 . 4 0 �-- -i--·-�------ -t-- -- -+- ---- 1·- ---

1 0 . 0 0

3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Dra g

Fi gure A . l3- Conti n ued o

70 . 0 0

(DEGREES)

90 . 0 0 1 1 0 . 0 0

__ T_____ ·-----�-T------------�------T--� I I I

-0 . 10 I I 1 --1� --------r-------1---------4, I I I '

� - o · 20 II ----+ symbol RN ( x !Ch 1----------j

}:l I 8 0 . 25 ! I 8 · I 0 . 50

� i 0 . 75 r0 . 30

I I � -0 . 40+------l----l-----t -�+ L I � I I '·, , I I @ ·-., I I � -0 . 50 _ _ \ -l-----1 \ I

-0 . 60+---- '�} -+-----t-----·--- -- ----- -----�-- �:::::---i

-0 . 70+---�--+---�--+---�--+---�--+---�--+--�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

(c ) P i tchi n g Moment

Fi gure A . 1 3:- Concl ude d .

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

1-lL H _j

2 . oo�-�---r- ----l I I .

-l------r---� ! i I

I I I I I

1 . 80+----r---- i --- -- --: I : l -6 r--------------4 Symbo l RN ( x 10 ) 1 ! �------------ I 0 . 25 :

1 . 2 0+------

0 . 8 0

0 . 4 0

I I I I --- -�----- - --t I I

0 0 . 50 I

_ 6 _ To:.75__ __ __ 1_ --- ·- ---i I : I I ! . i I "" ! i !

------ - --+--- --- ·--- - -�-----�- - --�- - - - ---- - · · ·+--- -------� i I I "' I ! I I I � : l I I : I ; I 1 1 ·, : I

0 . 0 0+-----,dr----� ---·--+---- - --+ ---- - -f- ----- --�.- - --1 I I i : \ I I I I I \ 1 -----r-------i------ f------- t- --- - ·r· -- --- ,

i I . I i I . - 0 . 8 0+---�--�--------�------�---.--�----.---+---.---4

- 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 A N G L E OF A T T A C K

. ( a ) L i ft

7 0 . 00 (DEGREES)

90 . 0 0 1 1 0 . 00

F i g u re A . 1 4 - Aerodynam i c Coeffi c i ents of the NACA 4409 Ai rfoi l � AR = 1 2 .

f-z w H u H lL lL w 0 u

(.!) <( a: 0

2 · 8 0 -r-----r--- - --r- - ---r---�-r - ------ --�----l 2

4 0 +--------t�--- --t-- symbol ' RN ( x 1D6 l �-- -----T--�--1 2 . 00 +----

I I ' I : � :�� l +-I 1 · ----- ·--r 6 i o . J s [-�------· --l

1 . 6 0

I 1 1 ! I i I � � +---- __ j _ _ _ _ ----+------- ---�----·-----t--,L -----+-- ·---- --� 1 1 1 /r 1 1

1 . 20

I I / I I I

� - -- 1---l ----- ---4 -- '�-�----�1- ---� I I !

o . 8 0+-----J-.. �--l-- - l�----------�--- -- --·-- I I , I � , I I ! I I i I I I 0 . 4 0 -+-------- �, - ----- -r - -- --- - /- ----- - ! - --- ----+- � I I I I , I o . oo+-�.-��--�--�--�--�--�--�--�--�--�� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF A T T ACK

( b ) Drag

Fi gure A . l4- Conti nue d .

7 0 . 0 0

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

-0 . 80+---

-0 . 70+---�--;---�--�--�---+--�--�--�--�r---�� - 1 0 . 00 1 0 . 00 30 . 0 0 50 . 00

ANGLE OF ATTACK

( c ) Pi tch i n g Moment

Fi gure A . 14- Concl uded o

7 0 . 00

(DEGREES)

90 . 00 1 1 0 . 00

2 . 0 0-r-----

1 . 60 �------4------. T � --�

_::.Sy�m_bo_l __ R_N _(_x -1�� " 0 . 25 � I I o o . 5o 1 ! 8 0 75 �--- ' "' 1 : oo 1

I \ I -l

\. ', --+----·--4--------",:-1

- 0 . 80+---�---+--�----�--�--�--�---4----�--+---�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 0 0 1 1 0 . 00

Fi gure A . l5� Aerodynami c Coeffi ci ents o f the NACA 4409 Ai rfoi l , AR = 9 .

2 . SQ .,---- ----T--�r -- 1 2 . 4 0+--------+--.. _L1 l -+-� ------1 I I I

Symbol RN ( x 1�6 ) I I

0 . 25

0 0 . 50 1 � I 6 0 . 75 I � 1 . 80+-------t--- --+--- '\'7 1 . 00

. J------=:=-ifl!H-1 -��:;r-----11 lt I i 'I � 1 . 2 0+----·--+- �r---/·---+----t----1111 � I

0 . 4 0 +------+-

o . o o+-�.-��--�--+---�--+---.---�--.---4---.-� - 1 0 . 00 1 0 . 00 3 0 . 0 0 5 0 . 00 7 0 . 00 90 . 0 0

ANGLE O F ATTACK (DEGREES)

( b ) Drag

Fi gure A . l 5 - Cont i nued .

1 1 0 . 00

Symbol RN (x io6

f- -0 . 20+-----+-z w H (J H lL lL � -0 . 30+--------t u

fz w :E 0 � -0 . 40-+-----r-

8 0 6 9

0 . 25

0 . 50 ! � : �� I -�---� I I ---_ -t i � � t-� - I a. -o . 50+------+-·---l-----i-- 1

-0 . 80+------1-------�-------��------+

- 0 . 70+---�---+--�----�--�--�---r---4----�--+---�--� 1 1 0 . 0 0 - 1 0 . 00 1 0 . 00 3 0 . 0 0 50 . 00

ANGLE OF ATTACK

Fi gure A . 15· Concl u ded .

7 0 . 00

(DEGREES)

90 . 00

2 . o o-.-----1 i I I

--1--T--' I 1 I l

1 . 60+--------t--- I i ·-r-----l--------�-- ---� I Symbo 1 RN ( x 106 ) \ 1 1 o o . 25 : 1 I l I 1 o o . so 1 . 20+------+------------,·--------l--- 6.

I I I , _ t � 1 i

0 . 7 5 1 . 00

r 1\ ! I X7 r- • \ ' g 0 . 8 0 +------ - Jf - - t� l . - � - �--- --+- - - ··--i

� I I I �� I t 0 . 40 \ �

0 . 00+--�-�-�---+l _J ___ _ J __ __ ->t __ J I l i \\\ I i ! . I I \ ' '

-0 . 80+---�--�--�--�}-----�--�--�---4----�--+---�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 0 0

ANGLE OF ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00 1 1 0 . 0 0

F i gure A . l 6- Ae rodynami c Coe ffi c i ents of the NACA 4409 Ai rfo i l , AR = 6 "

2 . 8 0 ...---------r------r ___ 1 ____ ----� -

1 I 2 . 4 0 +------+------+ : ---�--------- -- -------� I i I I

I - I i I Symbo l RN ( x 10

2 . 00 +------J-----·j--- -- ---i�

G 0 . 25 ---------1 I 0 o . 50 I

� 1 . 80 +' -+-i1 : 1 �::; ___ r I

H I I I ! tt I I I a----i!=!-----=---l!J I .

y i 1 . 20+----� -----+--1---+ %'/ 1 0

I I I < I 0 . 80 +-----�------+--�-+-----+-----+-- ---1

0 . 4 0 +--------+--- ---------1--- -----l o . o ot-�.-��--�--�---t--�--�--�--�--��

- 1 0 . 0 0 1 0 . 00 3 0 . 00 50 . 00

ANGLE O F ATTACK

( b ) Dra g

Fi g u re A . 16 - Conti n u e d .

70 . 0 0

(DEGREES)

90 . 00 1 1 0 . 0 0

-1�--T----- - _ __ _ l _____ _

I Symbo l RN ( x 106 ) l -0 . 1 0+--�-;:;;t:;=-!----"'f\\---t--------·-+- !3 0 . 2 5 ! �--�-·-----1 I I 0 0 . 50 I 6. o . 75

r- -0 . 20 z

9 1 . 00 1 -T--�1--1 w H u H lL lL � -0 . 30�--u

::E 0 ::E -0 . 4 0+------+------1,..----· (!) z H

I u r-H

-� I I \ I I \ I --+----__j----�+_____J � -0 . 50+------r--------�-------,_ ______ -+--------+-------�

-0 . 80+--------r-- ----�----- -1----- ------

-0 . 70+---�--�--�----1�--�--4---�---+--�----�--�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

Fi g ure A . 1 6· Concl ude d .

70 . 00

(DEGREES)

90 . 00 1 1 0 . 00

2 . 00r;��

B . L . Tri p

He i gh t : 0 . 127 mm

1 . 80 Locat i on : 5% Chord , Upper Su rface

10% Chord , Lowe r Surface

l-Symbol

----0 0 6 \'l

, .-I RN ( x io6 ) 0 . 25

0 . 50

0 . 75

1 . 00

� 0 . 80+-----��-- ·-+---+----- -----·�--------� H LL LL w 0 (.)

t 0 . 40�---�� H ...J

' \ l \

-+------+----4---1 ---�-----�

-0 . 80+---�---+----r---+---�---+--�r---+---�---+----r-� - 1 0 . 0 0 1 0 . 00 - 30 . 00 50 . 00

ANGLE OF ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00

Fi guee A . 1 7- Aerodynami c Coe ffi c i ents of the NACA 4415 A i rfo i l wi th Boundary Layer Tri p , AR = oo •

1 1 0 . 0 0

.__ z w H CJ H LL LL w 0 (J

(.!) < a: 0

� • tjU] I r --------'

2 . 4 0Li Symbo l RN (x io6 ) G 0 . 25 0 0 . 50 6 0 . 7 5 I I \-1 1 . 00

2 . 0 0

1 . 60 -t------+- -+--

1 I 1 . 20 +--------4�-------�------�+-----·--�---------r------�

0 . 80 +-----+-- ---+--�-- B . L . Tri p

1 0 . 0 0

He i ght : 0 . 1 27 mm Locat i on : 5% Chord , Upper S u rface

10% Chord , Lowe r Su rface

+--------��·-----�-----�

3 0 . 00 5 0 . 0 0 90 . 0 0 1 1 0 . 0 0

ANGLE OF ATTACK

7 0 . 0 0

(DEGREES)

( b ) Drag

Fi g ure A. l7- Cont i nue d "

Symbo l

f--0 . 20+-----+- ·-----+---=>�-

0 . 25 z w H u H LL LL

0 0 . 50

0 . 75 I � -0 . 30+------+--------+----

1 . oo 1 --T r---1 u

f-z w L 0

I I L -0 . 4 0+------+- ------1- ----1--� t!l z H I u f-H

' I I � -0 . 50+-------�-- ------�------�---------��--�r--------�

-0 . 80+------l

B . L . Tri p

Hei ght : 0 . 127 mm

Locati on : 5% Chord , Upper Surface 10% Cho rd , Lower Su rface

-0 . 70+---�---+----r---+---�---+----r---+----r---4----r-� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

( c ) Pi tchi n g Moment

70 . 00

(DEGREES)

Fi gure A . 1 7 .. Concl u de d .

90 . 00 1 1 0 . 00

1-z w H (.J H 1L 1L w 0 (.J

1--1L H _J

2 . 00...----- ---·r-----T��-, ' I I

Symbol

1 . 60+--------r-- ---+- 0 . 25 r------- -RN � X io6 ) 1 l'

0 . 80

0 . 40

r-··-- , I ----L

1 0 . 50 !

o . 75 I 1 . 00 I i

-.;---------,.-----� I

0 . 0 0+-�r----+--------+-------- +--- L ___ _

B . L . Tri p

Hei ght : 0 . 1 27 mm

Locati on : 5% Chord , Upper Surface \ ----r 1 0% Chord , Lower Su rface _ _ ___ \�\_,�1 -0 . 80+---�---+----r---+----r--�----r---;----r--�----�--�

- 1 0 . 00 1 0 . 00 3 0 . 00 50 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 00

(DE GREES)

9 0 . 00

Fi gure A . 18- Aerodynami c Coeffi c i ents of the NACA 441 5 A i rfoi l w ith Boundary Layer Tri p , AR = 1 2 .

1 1 0 . 00

B . L . Tri p �--J

He i ght : 0 . 127 mm

Locati on : 5% Chord , Upper S urface

10% Chord , Lower Su rface ! 2 . 4 0+-------+-- ----+----- I

Symbol 2 . 0 0+------�-------1 0

§ I 0 6

0 . 25

0 . 50

0 . 75

1 . 00 � 1 . s a -----� i 1 . 2 0+------+----�--t�--+- -�1--------- ___ _,I

0 I I -f-----1------t-------J(jjJ-----l-----+-- I . 1,1 o . so T-------1 ' I I

0 . 4 0+--------+--------7�-------+---------+------ -t

1 0 . 00 30 . 00 50 . 00 7 0 . 00 9 0 . 0 0 1 1 0 . 0 0

( b ) Drag

Fi g u re A.l8- Conti nued .

Symbo l 0 . 25 ,I 0 0 . 50

Zr- -o . 20 8 0 . 75 L __ __j

� 1 . 00 � � I

� �-�- -----�-��-�--�·---l' � -0 . 30-.-- -CJ

� \ I � 0 � -o . 40+------+-----�-------+------T � -0 . 50 . . - -�L I �----"-.d.

B . L . Tri p -t--1 He i gh t : 0 . 1 27 mm I Locati on : 5% Chord , Upper Surface J

_0 • SO+-----+--------� 1 0% Chord , Lower Su rface �·----! I I

-0 . 70+---�---+----�--+----r--�----r---�---r--�----r---� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 70 . 00 90 . 00 1 1 0 . 00 i

Fi gu re A . 18;.. Cone 1 uded .

1-z w H CJ H lL lL w 0 (J 1-lL H _J

2 . 00 l---

1 . 80

1 . 20

0 . 80

0 . 40

0 . 00

--l ----, I l I I

Symbo l RN ( x io6 ) 8 0 . 25 0 0 . 50 6. 0 . 75 Y! 1 . 00

I I I I � B . L . Tri p I I

He i ght : 0 . 127 mm

Upper Surface I Locat i on : 5% Chord ,

10% Chord , Lower Surface �

-0 . 80+---�---+----r---+----r---+----r---+---�---+---.r---1 - 1 0 . 00 1 0 . 00 3 0 . 00 50 . 00

ANGLE OF A TTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00

Fi g ure A . l 9.- Aerodynami c Coeffi ci ents of the NACA 4415 Ai rfoi l wi th Boundary Layer Tri p , AR = 6 .

1 1 0 . 00

2 . 80-r----�--�-, l 2 . 4 0+-------+--j __ l,.

II --"S y_m_bo_l __ R_N___:_:_( x.:.__1 "6_6..:.._) I I 8 0 . 25

i ' 0 2 . 00+--------;----+-------t-- 8

0 . 50

0 . 75

1 YJ 1 . oo 1 ._ I I �, � 1 . 60 I, �� B . L . Tri p L_j H I He i ght : 0 . 1 27 mm �----- ·· -� lt ! '! Locati on : 5% Chord , Upper Surface

, 8 I 10% Chord , Lower Su rface ! � 1 . 20+----+-+

� I 0 . 80+----- -1-------J-

1 0 . 00 30 . 00 50 . 00 ANGLE O F ATTACK

( b ) Drag

Fi gure A . 1 9- Cont i nued.

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

I--0 . 20

z w H tJ H LL LL � -0 . 30 tJ

I-z w L 0 L -0 . 40 l!l z H I tJ I-H a. -0 . 50

I I I I I I -I I I t I Symbol

B . L . Tri p

Hei ght : 0 . 127 mm

0 . 25 .

0 . 50

o . 75 ,

1 . 00

-0 . 60+-------+---------�

Locati on : 5% C hord , Upper Surface

10% Chord , Lower Su rface . ---�

-0 . 70+---�---+----.---+----r---+----.---+----r---+------� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

Fi gure A. 19- Concl ude d o

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

1-z w H u H lL lL w 0 u 1-lL H _J

2 . 00

1 . 60

1 . 20

0 . 80

0 . 40

0 . 00

----r- -�---l-! !

-�--l .

Symbo l

L----t-----+--B . L . Tri p

Hei ght : 0 . 1 27 mm

Surface

Cl ean

B . L . Tri p

Locat i on : 5% Chord , Upper S u rface 10% Chord , Lower Surface

. - -� -- - ·· - - --.- -·

_J I ! I I I

-·-� I I I _j I

-0 . 80+----.---+----r---+----.---4----r---1----r--�----�--� - 1 0 . 00 10 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

(a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi gure A . 20- Effect o f Boundary layer Tri p on Aerodynam i c Coeffi c i ents o f the NACA 4415 A i rfo i l , AR ::... oo , RN = 0 . 25 x 1 06 o

2 . 80....----� l-----1 -T------- ---� . I I , 2 . 40+------- -t 1 ------t---- r-1

I l Symbol S urface 2 . 00+-------� ��---------I

� I � 1 . 60+------ r-

C l ean

B . L . Tri p I I . ! I I ; ----r------r---1 H ! lL lL w 0 CJ

� 1 . 20-+--------� rr 0

I I I I I I ----+--�-----�-1 1 I

0 · 80+----+-·-+----r:�-----r B . L . Tri p

0 . 40-+---------+-

1 0 . 00

He i ght : 0 . 1 2 7 mm I Locat i on : 5% Chord , Upper Surface

30 . 00 50 . 0 0 ANGLE OF ATTACK

( b ) Drag

Fi gure A . 2d- Conc l ude d o

70 . 00 (DEGREES)

90 . 0 0 1 1 0 . 00

..... z w

2 . 00�--r---� ____ 1 1 1 . 60+-------�-� ··�·-----t------11

1 . 20-+---------«

� ---------�---- J ___ _j � I !

I I I I l

tj 0 . 80+------Hl'-+ II _ ___ ___ L_�----+� H lL. lL. w 0 tJ

Symbol Surface I 1 . · EJ C l ean 1 I

t: 0 . 40+-----1---+---I 0 B . L . Tri p t � H

I 0 · 00+------jr=----+-------f------j- B . L . Tri p

! I I I I I Hei gh t : 0 . 1 2 7 mm , Locat ion : 5% Chord , Upper S urface

�-------+-------+-------�-------l�O_%_�c_h_or_d_,_L_o

e_r Surface 1

-0 . 80+---�--�--�----�--T--�--�--�----r---+----r---1 - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

(a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi gure A . 21- Effect of Boundary Layer Tr i p o n Aerodynam i c Coe ffi c i ents o f the NACA 4415 A i rfoi l , AR = oo , RN = 0 . 50 x 1 06 0

2 . 80-.------r --�--l� ----- ------2 . 40+--- -�1-------1----

--+------1 I j

I S urface i 1 �----C-1 e

_a_n __ �-----

B . L . Tri p

r I I ! I I

--l I l - I - I

r----r--1----1 +------+----·--+-...t---+ B . L . Tri p I He i ght : 0 . 1 2 7 mm

I Locat i on : 5% Chord , Upper Su rface 1

0 . 40+-------�------+r-------��

1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

Fi gu re A . 2 1- Conc l ude d .

10% Chord , Lower S u rface

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

2 . 0 0-r-------r- ,---l--

1 I I 1 . 80+-------+-----+----- Symbo l Surface _l ____ __.

Ill --=---G---c-1

a_n__ I 1

0 B . L . Tri p ! 1 1 . 20+-----�1 ��--+-- ·-- J __ � I I

� 0 . 80 --+------+--+--t-� � I ! I 8 I i I I t 0 . 40+----¥---+-------i------1·-- _j I I � I I I I I

0 . 00+---,1-----+-----+-----B . L . Tri p

Hei ght : 0 . 12 7 mm I

1 Locat ion : 5% Chord , Upper Surface ___ L ____ � O% Chord , Lowe r S urface I I . '

-0 . 80+---.---;---�--�---.---+---.---4---,----�--�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF A TTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi 9 ure � . 22- Effect of Boundary L ayer Tri p on Aerodynami c Coeft i c i ents of the NACA 4415 A i rfo i l , AR = 00 , RN = 0 . 75 x 10 .

2 . a or ___ r ____ l 1 1 I

2 . 4 0+-----t-----if----i � t I • i � 1 . 60+-----+----t-----+ Symbo 1

� I , : 0 CJ

� 1 . 20+--------+--------+-----a: 0

0 . 80+------+-----1--...a-----1 B L • • Tri p

-- -l I I I

Surface �-----t Cl ean I B . L . Tri p ,

I I � I Hei ght : 0 . 127 mm

1 0 . 00 30 . 00 5 0 . 00

ANGLE OF ATTACK

( b ) Drag

� ---·· l 7 0 . 00 . - 90 . 00

(DEGREES)

Fi gure A. 22- Conc1 uded o

1 1 0 . 0 0

1-z w H (..) H LL LL

. w 0 (..) ILL H

I 1 . 80+--------+---------+-------�--------�-------�--------�

1� r Symbo l S urface

c:J C l ean

0 B . L . Tri p I

1 . 20�/l' ��---+-0 • s o �"' . I -------,____

I l I I t---·-------j � I

0 . 40+-----t:B--+-----+------+------+-----·--+-----�

I I 0 . 00+-��"----+--------j�-·----i I B. l . Tri p 1 �-J - He ight : 0 . 12 7 mm l locat i on : 5% C hord � Upper Surface 1

I _ 10% Chord , Lower Surface -0 . 40T-<':L..------f------l--------+--·----+---·-----t--------l

-0 . 80+--�---+-��--+--�---+----�--+----r---4----�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 ANGLE OF A TTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi qure A . 23 - Effect of Boundary Layer Tri p on Aerodynami c Coefti c i ents of the NACA 4415 A i rfoi l , AR = co , RN = 1 . 00 x 10 o

2 . 8'"' ""

2 . 4 0

2 . 0 0

� 1 . 8 0 H lL lL w 0 CJ

� 1 . 20 a: 0

0 . 80

0 . 40

( �- · 0 . 00

- 1 0 . 00

I l ) l I I I I 1 I I I I l I 1 l I I I

! I I I I I I I I

Symbol Surface i ' EJ Cl ean I I

I 0 B . L . Tri p I I I I I

I B . L . Tri p

I He i gh t : 0 . 127 mm

Locat i on : 5% Chord ,

r. 1 0% Chord ,

/ 1 0 . 00 30 . 00 50 . 00

ANGLE O F A TTACK

( b ) Drag

Fi g ure A . • 2J Cone 1 uded .

70 . 00 (DEGREES)

I ' I I l I � I � ' I

I I I I

Upper Surface

Lower S u rface

90 . 00 1 1 0 . 00

2 . 00-r----

1 . 80 i--;

Symbo l Surface

13 C l ean

0 B . L . Tri p

tj 0 . 80+---- ---t---------+---1 I H lL lL w

' O ' U

t 0 . 4 0+-----T--4--------� �· ! H _J

B . L . Tri p

He i ght : 0 . 12 7 mm

I Locat i on : 5% Chord , Upper S u rface

Lower Su rface I 10% Chord , - 0 . 4 �:;1----- ------ �--- ----1 I

- 0 . 80+---�--��------�--------+---�--��------�---.�� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 0 0 7 0 . 00

( a ) L i ft

9 0 . 00 1 1 0 . 0 0

Fi gu re .A . • 24- Effect of Boundary Laye r Tri p on Aerodynami c Coeffi c i ents of the NACA 4415 A i rfo i l , AR = 1 2 , RN = 0 . 25 x 1 06 .

fz w H u H lL lL w 0 u

(!) <! a: 0

2 . 80 -r--------r-·----------- - -l · --·--------r· ·----- - _ __ l _____ -- ------r- - - - -� I ' I I I i I I i i I : ' I i ! I I i ! II 11 I I L I ' 2 . 4 0+---- ---------r--·---------·--· - ---------------t- --- - - - - - - - -L...-... - -- - - -- +-------·---------l I I I I ! l ! i Symbol Surface 1· ' I I ! ' El Cl ean ! ! I

-+--------------- L-. _j _ _____ _ _ j_ 2 . 00 ! i i 0 B . L . Tri p �-- -----�

I I I I I I i I l I

' I I i I

I I l I I I I I

1 . 60+----l ---- ---r--�----' I ,i l I I ! ! I I i

1 . 20+--------- --l·- - --- ------ ,------ ----1 ----- --, ------�--:------- ---� I · i i i I ! t I I I . ' I I l I ! I I , ! !I I I

0 . 80+------....__.,�1--- -·-r

· ----

B . L . Tri p �� He i ght : 0 . 1 27 mm

I Locat i on : 5% Chord , Upper Surface I _____ _ J __ ____ ___ �--------- 10% Chord , Lower Surface j

I I I i

0 . 00�� -��-��1 ��I - 1 0 . 00 1 0 . 00 3 0 . 00 50 . 00

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 24- Concl u ded o

70 . 00

(DEGREES) 90 . 00 1 1 0 . 00

1-z lU

2 . 0 0-p------------��· ......:Sy::...m...:.b..:..o..:...l __ s_u_r_f_ac_e_ 1 . 60+-------�·--------}---------�

G Cl ean 0 B . L . Tri p

� 0 . 80+-------��-------+--·------4---��--�-------+-------� H LL LL lU 0 u

t 0 . 40+---��------�---------4---------l---------+------� H ....J

0 . 00+--4----�--------�------� B . L . Tri p He i ght : 0 . 127 mm Locati on : 5% Chord , Upper S urface

10% Chord , Lower Surface

-0 . 80+---�---4----r---4----r---4----�--�--�--��--�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 ANGLE O F ATTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi gure A . 2S- Effect of Boundary Layer Tri p on Aerody11ami c Coeffi ci ents .

· · of the NACA 4415 Ai rfoi l , AR = 12 , RN ='= · 0 . 5 0 x 106 .

8 8 I :

2 . 80��

--T ---T · ---,�-, II ---+--- _..._ ___ +-�------+� -----��• 2 . 4 0+----

Symbol Su rface

1 1 o Cl ean 1 j i t I I I

2 . 0 0+------1-------- - 0 B . L . Tri p

r-------i· ----------1 I ! I I � I i I � 1 . 6 0+--- ---+. ---- �-� it I I I 8 I I I � 1 . 2 0+----- -+-------+--------+--/ - -+-----r------ i

0 I I I I I 0 . 80 +------�---- B . L . Tri p

He i ght : 0 . 1 2 7 mm

0 . 4 0+------+-------J...I----- Locati on : 5% Chord , Upper Surface

10% Chord , Lower S urface

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 ANGLE O F ATTACK

( b ) Drag

F i g ure A . 2 5 - Concl u ded .

7 0 . 0 0 (DEGREES)

9 0 . 0 0 1 1 0 . 0 0

..... z w H tJ H IJ... IJ... w 0 tJ

..... IJ... H _J

2 . 00�------� ---- ·-- --·--�

1 . 60+-------�L-------�

0 . 80

0 . 40

0 . 00+-��---+---------+--------4

-0 . 40+-------��------� -------�

Symbol

Surfa ce

C l ean

B . L. Tri p

B . L . Tri p

He ight : 0 . 12 7 mm

Locati ofl : 5% Chord , Upper Surface 1 0% Chord , Lower Surface - - - --- -----------l

-0 . 80+---.----r--�--��--�--�--�--�----�--+---�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

(a ) L i ft

70 . 00 {DEGREES)

90 . 00 1 1 0 . 00

Fi �ure A . 26- Effect o f Boundary Layer Tri p on Aerodynami c CZoefti c i ents · o f the NACA 4415 A i r fo i l , AR = 1 2 , RN = 0 . 75 x 1 0 .

2 . 8 0...-----1 �----r----r-�-r--- �

i ! i' I I . 2 . 4 0 -+-------+-

, --------1�- - - -------r---------r--- I I I I I I I I I

1 8 ��::;ce L----�

I 0 B . L . Tri p I � 1 . 60+------+---- ·--+--------1-------r------+-- �_J H � I g I I I ' � 1 . 20 4-----il--!---+-� --�----�-� a:o

I I I I I I

I I I I I

0 . 80 ...__----t------+----w----t B . L . Tri p

0 . 4 0+--------4----

1 0 . 0 0

I He i gh t : 0 . 127 mm I Locat i on : 5% Chord , Upper Su rface

I 1 0% Chord , Lowe r S urface l - --- . .. � ·

3 0 . 0 0 50 . 0 0 7 0 . 0 0

( b ) Drag

Fi gure A . 26- Conc l uded .

9 0 . 0 0 1 1 0 . 0 0

1-z w H CJ H I.J... I.J... w 0 CJ 1-I.J... H _J

2 . 0 0

1 . 80

1 . 20

0 . 80

0 . 40

0 . 00

� j I

;J -0 . 4 0

-0 . 80 - 1 0 . 00

··-�· --·�-·-

I -- I •,_ r\ S}::mbo 1 Su rface r �� G Cl ean

k 0 B . L . Tri p � I I ! 1 -1 ! I I -

I I I I B . L . I Tri p

I He i ght : 0 . 1 2 7 mm

I Locati on : 5% Chord , Upper S u rface I I 1 0% Chord , Lower Su rface ----- ----w- - --

r 1 0 . 00 30 . 0 0 50 . 00 90 . 00 1 1 0 . 00

ANGLE OF ATTACK

70 . 00

(DEGREES)

( a ) L i ft

Fi gure A . 27- Effect o f Boundary Layer Tri p on Aerodynami c Coefti ci ents of the NACA 4415 Ai rfo i l , AR = 1 2 , RN = 1 . 00 x 10 •

(.!) <! a: 0

2 . 8 0�---�---·---l--------,------ - 1--------�----, : I I I I I . 2 . 4 0 +------l-----l ----1---- ----t - ---J ---�

! I I I I

i I I I I ! I. I I I I I

2 . oo�------+1------ ! _ _j _______ J _ _ __ _ _ _ __ j _ _ _ ____ j II ! i :

1 . 6 0

1 . 2 0

' I I I I , . I I ' I I ' , I I i I I I . ! I i L --+-----r------_j1--- symbo 1 surface 1 I I 1 I EJ C l ean

+--------1� ---- --- �-__ j__ 0

B . L . Tri p r·

' I I ! I I

0 . 8 0+----------li! ______ __ J_ j i

I I B . L . Tr i p

0 . 4 0 +----

I I I : r 1 He i ght : 0 . 1 2 7 mm i I I I Locati on : 5% Chord , Upper Su rface

10% Chord , Low�r Su rface

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 ANGLE OF ATTACK

( b ) Drag

_ ____ T ____ _ r ____ _

7 0 . 0 0 (DEGREES)

9 0 . 0 0

Fi gure A . 27- Concl uded o

1 1 0 . 0 0

2 . 0 0.,.---------,-------r---- -·l -1--�--1 I I

1 . sor--------+--------+-------�l--------+-

1 . 20t--------+--��+-------�-· �Sy�m=b�ol��S�u�rf�a�ce� El C l ean

0 B . L . Tri p

B . L . Tri p

Hei ght : 0 . 12 7 mm

Locati on : 5% Chord t Upper Surface

1 0% Chord , Lower Surface

-0 . 80·��.---+---.---+---�--+---.---4---.---�--�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 70 . 00

(DEGREES) 90 . 00 1 1 0 . 00

ANGLE O F ATTACK

( a ) L i ft

Fi gure A � 28- Effect o f Boundary Layer Tri p on Aerodynami c Coeffi ci ents

of the NACA 4415 Ai rfoi l , AR = 6 t RN = 0 . 25 x 106 •

fz w H

(.) H IL lL w 0 (.) (.!) < cr a

2 . 8 0 -r-------r--·- -- r-·- · - -- - --- - -- r-------- -- - ----- ---- ------r----1 I , I I !

: I I I I I ) I I I

I I i I ! ! I j 'r • :

2 . 4 0 +-----+------ --- � ------ ----· · · - · ·t·---- ------- - - -1-- - - - - - - · ' I , f i I . ' I !

I _ _ _ _____J I I I I

I I I I I I ; i I ' ! I I

0 0 +--- - 1 - - ---r----- -r - -----�-- ------- - T·--- - -: ' , I I I I I I ' 1 . 8 0 +------+- -----�--- Symbo l Surface --- -·� - ------1 I / �-

G-----

C-l e_a_n __ _

I I I 1 . 2 0 +-----J- ·- ·· - --·· t - --- - · · _ ___ : __ · r -�L �-��:� , ___ _ j I Ji I ! I I ! l I 0 . 8 0+------ j - - -·--- - -

-- -- -- --!--- · --·- -· l- - ---� i I I I I j I I

1 0 . 0 0

B . L . Tri p Hei ght : 0 . 127 mm

I I I I I Locat i on : 5% Chord , Uppe r Surface 1

3 0 . 0 0 5 0 . 0 0 ANGLE OF ATTACK

( b ) Drag

Fi g ure A . 28- Conc l u ded o

10% Chord , Lower Surface

7 0 . 0 0 (DEGREES)

9 0 . 0 0 1 1 0 . 0 0

1-z w H (J H lL lL w 0 (J 1-lL H _J

2 . 0 0�--------,--------� �--·--1 I

1 . 80+----· ----+---·----+-----·----�-1. I 1

I I ... - - - · -·--t---- -·-----;

I I I i I I I I I I I I :

Symbo l S urfa ce

C l ean

. I : . I 1 . 20+----- --+---��- t-

G 0 B . L . Tri p l---------i )

! l I ! 0 . 80

I 0 . 4 0 ---t--·--+-----1------.!-----··

I I I 0 . 0 0 -+------Cfl-.---

l-----t-----

B . L . Tri p

He i gh t : 0 . 127 mm 1 Locat i on : 5% Chord , Upper Su rface

1 0% Chord , Lowe r Su rface -·-- .. .. . . - ---- ·-·--r-

-O . B0+----.---4----.---�--�----+----.---4----�--�--�--� - 1 0 . 0 0 1 0 . 00 3 0 . 00 50 . 0 0

ANGLE OF ATTACK

( a ) L i ft

7 0 . 00 (DEGREES)

90 . . 00 1 1 0 . 00

F i g u re A . 29- Effect of Boundary Laye r Tri p on Aerodynami c Coeffi c i ents of the NACA 4415 Ai rfo i l , AR = 6 , RN = 0 . 50 x 1 06 •

1-z w H u H

lL lL w 0 u (!) <! !I 0

2 . 80 �---- -- �------------ �- - - - _ _ _ _______ l _ _ _ _ _ _ _ .. __ __ l ____ __ __ _____ _

I I I I · i I i I I I I ! I I I : I. I ! I 2 . 4 0 +----- --+-------- +- --- - - - - - - - - - - - - - - --+ - -- - · -- - -- -----+ - ·- ----- ·-----1 l I I ! I ,

i i - - - · ----------1 i I l

i I 2 . 00+----- ·-----j--- ·------- - -·--- - - ---- - --- Symbo 1 S u rface --- - -------1 ��---------- j

i I ' I I

G C l e a n 1 : 0 B . L . T r i p .

I ' I 1 . 60+-------+--- ----+------ ----l- - I

- ---- ------------r--- ------1 1 ' . I I I ! ! I I ! I I 1 1 I I i ; I I 1 . 2 0+----- -- -+---- -----t-- ------t-------+-- - - -- ----- T---- - -- --l I i VI . I : I ! i I ! I I I ! I I

0 . 80-4-------�---- ---- ---+--- --! - ---------+------+--------� I i i I I I I i ' I I I

, B . L . T r i p

0 . 4 0+------------ ---------- - He i g h t : 0 . 1 2 7 mm

1 0 . 0 0 3 0 . 0 0

Locat i o n : 5% C h o rd , U p p e r S u r fa ce 10% C h o rd . Lowe r S u r fa c e

50 . 0 0 90 . 0 0 1 1 0 . 0 0 A N G L E O F ATTACK

70 . 00 (DEGREES)

( b ) Dra g

Fi g u re A . 29 - C o n c l u de d .

2 . 00�--l T -l I I I 1 . 60+-----+----r�-----+ _ _ __ l I : I I I I l -+--------� �S�ym�b�o�l ____ S�u�r_f_ac�e�---l

EJ C l ean

0 B . L . Tri p

� 0 . 80+-------��H lL lL w 0 (.)

t 0 . 4 0+-----�._, ________ �--- I --l--- -�- -----�

0 . 00+--4�---4--------�-------- B . L . Tr i p

He i ght : 0 . 1 2 7 mm

L ocat i on : 5% Chord , Upper Su rface 1 0% Chord , Lowe r S u rfa ce

-0 . 40+-----+--- ----+---- --- --------+------.-----

-0 . 80+---�---4----�--�---,----+---�---4----�--�--�--� - 1 0 . 00 1 0 . 00 30 . 00 5 0 . 0 0

ANGLE O F ATTACK

( a ) L i ft

70 . 00

(DEGREES)

9 0 . 00 1 1 0 . 00

Fi q ure A . 30- Effect of Boundary Layer Tri p on Aerodynami c Coeffi c i ents -of the NACA 441 5 A i rfo i l , AR = 6 , RN = 0 , 75 x 1 06 •

2 . 80

2 . 40

2 . 00

1-z w H 1 . 60 u H LL LL w 0 u l!l 1 . 20 <t a: 0

0 . 80

0 . 40

----T�-- r- - �l -+--- _j I I I I I I I _L i

_ _J L Symbol Su rface I l I I I El C l ean J I 0 B . L . Tri p i I I � ------- � -I i I I I I �--� I

I I I I I I ' I I I I I I I I I I ---, I B . L . Tri p

------- Hei g h t : 0 . 1 27 mm

Locat i on : 5% Chord , Upper Su rface

1 0% C hord , Lower Surface

1 0 . 00 3 0 . 00 50 . 00 7 0 . 00

(DEGREES)

90 . 00 1 1 0 . 0 0

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 30- Conc l ude d .

I-z LJJ H (.J H' I.J... I.J... LJJ 0 (.J

I-I.J... H

1 . 60+-------��---

1 . 20 -- - Symbo l S u rface

[!] C l ean 0 B . L . Tri p

0 . 80 '

0 . 40 J_ I

0 . 00+-��--t------- B . L . Tri p

Hei ght : 0 . 1 27 mm

1 -0 . 40+-------i Locat i on : 5% Chord , Upper Su rface

1 0% Chord , Lowe r Surface

-0 . 80+---.r---+---,r---+---�--�----r---4----r---4----�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

(a ) L i ft

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

Fi gure A. 3 1- Effect of Boundary L ayer Tri p on Aerodyn ami c Coeffi ci ents o f the NACA 44 15 Ai rfo i l , AR = 6 , RN = 1 . 00 x 1 06 •

1 () ()

r-z w H (.) H lL lL w 0 (.) (.!) <( a: 0

2 . 80-r-----·-y

2 . 40+------+------+-----+- -----+------1'-- -------1

2 . 00

1 . 60

1 . 20

0 . 80

0 . 40

_J_ ·

1 0 . 00

;;.__ -�--------- - -

Symbol S urface

G Cl ea.n i ' I 0 B . L . Tri p t

I _J I I I I I I ! I I -+ I I � ! I I t-' 1 I B

I I L . Tri p ---+ Hei ght : 0 . 1 27 mm I Locat i on : 5% Chord , Upper S urface I

1 0% Chord , Lower Su rface

30 . 00 50 . 00 90 . 00 1 1 0 . 00 A NGLE OF ATTACK

70 . 00 (DEGREES)

( b ) Drag

Fi gure A . 3l - Concl uded .

r--z w H tl H LL LL w 0 tl r--LL H ..J

2 . oo�-----r-�

Symbo l AR I 1 . so I

8 I n fi n i te :--

0 1 2 8 9 '\(/ 6

1 . 20 r-0 . 80

0 . 40

I -0 . 4 ll.flllr-------+------ ----+----+-----o . ao�-.--�-�--��-.--�---r--+---.r---+--.---�

- 1 0 . 0 0 1 0 . 00 3 0 . 00 50 . 00 70 . 00

ANGLE OF A TTACK (DEGREES)

( a ) Li ft

90 . 00

Fi g u re A . 32- E ffect of Aspect Rat i o on Aerodynami c Coe f[i c i ents o f the NACA 4418 Ai rfoi l at RN = 0 . 25 x 1 0 •

1 1 0 . 0 0

� · tiO-r------.---r-r -r�� ' 1 2 . 4 0 +-------+

,------1

1-----+---i:-----t---� I ! I I 1,· I I

AR I! ! I +-----+- _Sy,_m_b_o 1 _____ t------t-----7r--·-----+-·--�--t 2 · 00 i : :�fi n i te y � 1 . 60+------+------� -, ... : -1-t--�-=----t----............ .....::-----t i I tJ

� 1 . 20-+------+-a: 0

0 . 4 0+-----�-------�------r----------t---

o . oo·-��=--..----1-.......-J-�_J---.--L�_J - 1 0 . 00 10 . 0 0 3 0 . 0 0 50 . 00

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 32w Conc l uded .

7 0 . 00

(DEGREES)

90 . 00 1 1 0 . 0 0

1-z LU H (.J H LL LL LU 0 (.J 1-LL H _I

2 . 0 0 I I I 1 . so -i---I

1 . 20

0 . 80

0 . 4 0

Symbol

[!] 0 8

I n fi n i te r 12 I 9

___ _J_,_, !

-0 . 80+---�---+----.---+----r---4----�--4---�---4----�� - 1 0 . 00 1 0 . 0 0 30 . 0 0 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 00

Fi gure A . 33- Effect o f As pect Rat i o on Aerodynami c Coe fti c i ents of the NACA 4418 Ai rfoi l at RN = 0 . 50 x 10 •

1 (\ �

1 1 0 . 00

2 0 80·.,....-------.--------.-----...----�

Symbol 2 . 40 8

0 8. Y1

2 . 00

I n fi n i te 1 2 9

� 1 . 60+-------�--------�--�--4-��---+��ffi---�--� · H

ll.. w 0 tJ

� 1 . 20+--------+--------r------r��r-��------+-------� a: a

1 0 . 00 30 . 00 50 . 00 ANGLE O F ATTACK

( b ) Drag

1 0 5 I

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

i:::! . u u�----.---------.---� I

- 0 . 80+---�--�--�---+--�----�--�--�--�--�--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 00 ' 1 1 0 . 0 0

Fi gure A . 34 - E ffect of As pect Rati o on Aerodynami c Coefti c i ents · o f the NACA 4418 Ai rfo i l a t RN = 0 . 75 x 1 0 o

T 1 1 ---r 1 1 I I I I ' I 2 . 8 0 ......----

J I I 1 I I 2 . 4 0 +-- �--r---i----·---r-r ·-��. I I I I ' I I I Symbo l AR

2 • 0 0+---------+-1 ----r- r- --"--:-·. --...:....:.� �:...:__f-i n-i-te I i I ! I z t-- � ! I LU I I I � 1 . 8 0 --+------ : --�--

H I � I 0 . 8 0+-----

0 . 0�--��--��--�--�--�--+---�-4--�� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0

( b ) Drag

Fi gure A . 34 - Cone 1 uded 0

9 0 . 0 0 1 1 0 . 0 0

2 . o o �---.--------,.--------.-------

r---.. --l--· ··--1 I I I I I I I I

1 . so+----i-----+----L---·-+----L-�---1 I 1 I I l- I

I � Symbo l

-0 . 80+---.---�---.--�----r---+---�---+--�----�--�� - 1 0 . 00 1 0 . 0 0 30 . 0 0 50 . 00

A NGLE OF ATTACK

( a ) L i ft

70 . 0 0

(DEGREES)

90 . 0 0

Fi gu re A . 35 - Effect of As pect Rat i o on Aerodynami c Coefti ci ents of the NACA 4418 Ai rfo i 1 at RN = 1 . 00 1 x 10 "

1 1 0 . 00

2 . so -----��--

I --T--�T--T I i ! I I I ! I I I

2 4 0+-------_j ___ __j __ .. _____ ! "----�-----+----.. ·------L---- -----·---4 • I ! I i i I I I I I

I I i ! l Symbo l AR I I 2 . o o�-------r-------- -·----+----------�-� o

! I � � I

I n fi n i te ----1 2

9 6 it I I . H i . 6 0 -1------t- --- ---- ----t··---·------·····--·-+-·-· --- .. -- - - ---.. -;------· - ··--· ---· U I ' I H '

LL LL w 0 u

� 1 . 2 0-1---rr 0

0 . 8 0�------�------

o . 4 o-+----·

0 . 0�� .. ��---t--�--l---�-J--�--J---�� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Dra g

Fi g u re A . 35 - C o n cl u de d o

7 0 . 0 0

(DEGREES)

9 0 . 00 1 1 0 . 0 0

1-z w H u H

lL lL w 0 u 1-lL H _j

2 . 00 ..,.----l--------.-·-·-··----,-·-·--� ---� 1 . 6 0+-----1-

! ------+------+�---'Sy'-:-_b_o_l --�-�-f-i n

-i-t�e

r--------!

1 . 2 0

0 . 80

0 . 40

0 1 2 8 9 V7 6 -l� .. ----

o . oo�---�- ·---+----+----+----l [

-0 . 4 ur.M----+ \ \

-0 . 80+--�---+---,.---+----.--�----r---�---r--�----r-� - 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTAGK

( a ) L i ft

7 0 . 00

(DEGREES)

90 . 00

Fi gure A . 36- Effect o f As pect Rat i o o n Aerodynami c Coefti c i ents o f the NACA 4415 Ai rfoi l at RN = 0 . 25 \ x 10 .

1 1 0 . 0 0

2 . 80 .....----------- ---- -l-----r--T I .� I 2 . 40

2 . 00 t I

_,___AR-=---l--� --1·--· I n fi n i te I Symbol

8 0 8 'V

1 2 1 9 �------+----r---�-t-------1 I 6 !

I § -+-------1------+-·---fl_L/ --!!c +------tj 1 . 60 -------j H lL IL w 0 CJ �c 1 . 20.+ ._. · ----+---.,--,--1-----+--t----t'--Jt-----+-----t------t a: 0

0 . 40+-. -----t---..,----.,---�1--------t-· · ___ ._�+------

1 0 . 00 30 . 00 5 0 . 00

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 361- Cone l uded o

7 0 . 00 90 . 00 - .s

(DEGREES)

1 1 0 . 00 .

!z l.lJ

2 . 00

1 . 80

1 . 2 0

-,--I I -------+----� --I

-l-- l Symbol AR ! t

EJ I n fi n i te ----� 1 2 I

6 9 I 'V 6 I

� 0 . 8 0 H lL lL w 0 u t 0 . 4 0+-,--f!W---H _J

0 . 0 0 +---_ --+----+--L __ -t-------+------1 I I I 1 +------+----------t---·--+-----+---·--1 . ---�--l I

- O . B O +�r. --�---+----r---+---�---4----r---4----r--�----�� - 1 0 . 0 0 1 0 . 0 0 30 . 0 0 50 . 00 .

A NG L E OF A TTACK

( a ) L i ft

70 . 0 0

(DEGREES)

90 . 00

Fi gure A 37- Effect o f Aspect Rat i o on Aerodyn ami c Coefti c i ents •

of the NACA 441 5 Ai rfo i l at RN = 0 . 50 x 1 0 •

1 1 0 . 00

2 · SO....----------r-1---1-- --··· ·r -T--·--1-, I I I I I I 2 . 4 0 -+-----�-----r------�- r---

�b-o l

--"---AR

· - �----� I ! o I n fi n i te I I I i 0 1 2 · I

2 . 0 04-----+,-----------1f-------t- 8 9 f----� ! 9 6 I I

II 1 I ' I l-· I ' I ":__ i , I w : s · I � i . G O ---··· 1· - - r ··-- -�-L--->� - - - - -L-- - --- - - -r - ---- - -- - --------•

g ! I I � 1 . 204--------+----- t·--0 . 80+---

1 I �-----1---�-----r---------------+ I :

I 0 . 4 04-------1 --

1 0 . 00

I I I ------t---- - - -1

30 . 00 5 0 . 0 0 7 0 . 0 0 ANGLE OF ATTACK (DEGREES)

( b ) Drag

Fi g u re A . 37 - C o n c l uded o

90 . 00 1''1 0 . 0 0

1-z w H u H u.. u.. w 0 u 1-u.. H _J

2 . 00 1- l----I I

1 . 80

Symbo l AR

J__ B I n fi n i te 0 1 2

1 . 20 8 9 I I Vl 6

0 . 80

I 0 . 40 ---1-

I I 0 . 00 I

-0 . 80+---.----r---.--��--�--4---�---+--�----�--�� - 1 0 . 00 1 0 . 0 0 ao . oo 5 o . oo ?o . oo 9o . oo 1 1 0 . 00 I

( a ) L i ft

Fi gure A. 38- E ffect of Aspect Rati o on Aerodynami c Coefti ci ents of the NACA 4415 Ai rfoi l at RN = d . 75 x 10 •

2 . 40�-----+l-- I I I I i I I 1 I

2 . 0 0+------l----l- _j__ L__ �J I � I t; 1 . 80+--------1 ----+--· H I ---- -

8 �----r�----�----� 1 . 20 a: 0 !

1 0 . 00 3 0 . 00 5 0 . 0 0

ANGLE OF A TTACK

( b ) Drag

Symbo l AR I

El I n fi n i te 0 1 2

8 9 VI 6

7 0 . 00

(DEGREES)

9 0 . 0 0

Fi gu re A . 38- Conc l uded o

1 1 ti'. 0 0

lL w 0 u

- :,� -----�-r---l--· �-�� I I I 1 . 6 0+------�---------- -��------�---- - .1_ --------------,------·1

I I Symbo 1 AR 1 I j i 8 I n fi n i te 1

1 . 2 0 +-----tt-·��-\&---J--� - : �2 j ' I I \1 6 I I , I , '- ! 1 / 1' (:) f ! t I ·.. . ' i I i I . ·. to &-----A__ i I I ; -- - - - ---1- -- \=�� _-:� -- - - - - - �-- - -- - --- _L_ ---- -- - __ _ _ __j -�! '11 I! �v --·· - �� 11.

' ' ! I v I

j J I I § 0 . 4 0 +-----�d��------�,�-------�-------4--------�-------�

� ' I I I <� I I I l q�� I

- 0 . 4 0 _ ___ _.___! - - - ---- - · · - ·- --- -------.1.-------t··-··------i . I I

- 0 . 8 0+---�.----+---�--�--�--�r---�--�--�---+--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0

ANGLE OF ATTACK {DEGREES)

( a ) L i ft

9 0 . 0 0

Fi g u re A . 39- E ffect o f Aspect Rati o on Aerodynami c Coefti c i ents of the NACA 44 1 5 A i r fo i l at RN = 1 . 00 x 1 0 •

1 1 0 . 0 0

2 . 80�-r--�---r---- -- -r-�-- -- � -- -l--- -1 2 . 40�--�r--l�- --- �+----- 1- --- ---- r-----l

1 I i ! I I I I l I I 2 . 0 0+-----+----t·-----; s

ym:o�L_--:-R----t ---�.

� i . B0+-----1--------L�- l-- � �;f

i------1, � I 9 6 I [J_ I I - I � I I 1· I' LJ I i � 1 . 20 -r-----r----l--------�-�---·

0 . 40+-----+------"�------- ---1------- -------t !

1 0 . 0 0 3 0 . 0 0 50 . 0 0

ANGLE OF ATTACK

( b ) Drag

Fi gure A . 39- Concl u ded o

7 0 . 0 0

(DEGREES)

9 0 . 00 1 1 0 . 0 0

r-z w H u H lL lL w 0 u

r-lL H _J

2 . 00...----r- r --r--- ---r l 1 . 80 +---_11 ________ l _ _ __ _ __ J _ ____

Symobo l A

IRf. · t ,·-·- I

I 1 · n 1 n 1 e � f 0 12 I I 'I I I 8 9 II i I . \:1 6 I 1 . 20+---------+#1�\� �r�- '

! - -- r---� .\ I I 0 . 80

�\ __ 1 _ _ _ 1 \ i

0 . 40 --+-- -�------! I I

0 . 0 0 +----.JiMI----

-0 . 80+---�--�--�---+--�----�--�--4---�--�--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 0 0

ANGLE OF A TTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00

Fi g ure A . 40 - Effect of Aspect Rat i o on Aerodynami c Coefti c i ents o f the NACA 4412 Ai rfo i l at RN = 0 . 25 x 10 •

1 1 0 . 0 0

\--z ! U }--l u H LL lL w 0 u (.!) <! rr 0

I 2 . 4 0 +------L __ _

I 2 . 0 0 +---�+ -·

i . () f]

1 . 20

i i I i

i I I I

1 0 . 0 0

Symbo l

I n fi n i te !

3 0 . 0 0 50 . 0 0 70 . 0 0 ANGLE O F ATTACK (DEGREES)

( b ) Drag

Fi gu re A . 40 - Con c l ude d o

9 0 . 0 0 q, o . oo

2 . oo�---.....-------.---�-- 1

1 . 60 +----t---�1----+ ---- -----+------1

' Symbo l AR I 13 In fi n i te I : r I � 0 . 80T-----��--·--��r--+--------r-------� H ll.. ll.. w a (J t 0 . 40+---�RJ---- ------+-------li------f------f------1 H ..J

0 . 00+-��---r-------��------·+--------+--------�------�

-0 . 80+---,---�--�----�-----�--4---�---+--��--�--�--� - 10 . 00 1 0 . 00 30 . 00 50 . 00 70 . 00 90 . 00

( a ) Li ft Fi gure A . 41� Effect of Aspect Rati o on Aerodynamjc_ Coef6i ci ents

of the NACA 441 2 Ai rfoi l _at RN = 0 . 50 l x 1 0 "

1 1 0 . 00

1-z w H u H I.L I.L w 0 u

l') <t: a: 0

2 . 8 0....-------1--1 I 2 . 40-+------+!_____ I r-· ! I . I I

I l I I l l I I i I I I 2 . OO+-----i-----t- -

·--r,mbo l J_��- -�--� I i ! o I n fi n i te i I

1 . 60

1 . 20

' I I I ; 1 o 1 2

+-----+------t �-{-- ll::. 9

l I 'V 6 I

0 . 80+---

I 0 . 4 0+------+---ID/-

1 0 . 00 3 0 . 00 50 . 00

ANGLE O F ATTACK

( b ) Drag

Fi qure A . 41 - Concl ude d .

7 0 . 00

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

2 . oo�----1---

-0 . 80+---�--4---�--�--�---+--�---4--�--��--�-4 1 1 0 . 00 - 1 0 . 00 1 0 . 00 3 0 . 00 50 . 0 0

ANGLE OF ATTA CK

( a ) L i ft

7 0 . 00

(DEGREES)

90 . 00

Fi gure A . 42 - Effect of As pect Rati o on Aerodynami c Coeffi ci ents of the NACA 4412 Ai rfo i l at RN = 0 . 75 x 1 06 .

}-z !JJ H u H LL LL w 0 u

(!) <t cr 0

2 . a o ...----�T - �

1 ----r--�--�1-----1- -l I I I ! I !

2 . 4 0 +---- -i ·--- -----+- --1--------- t--- - �------� l l l l I I I i I :

2 . 0 0+------+ - - - -4-- - - ------L--- - +- - -� � I Symbo 1 AR i \

i . 6 0

1 . 2 0

i ! I f ' . t I' I 1 8 n 1 n 1 e 1 i I _ 0 1 2 I

i l � i i --- -t·--- --- --·�--�----- -- ---· I

- - & 9 '1 - ----- --- - ----� I i \-7 6 I I I I

I ,fo. I I ! -r� ---1-�- --�� :

I /» i l i

0 . 8 0 +---- �� -� �� J:_ _l _ _ _ _ t------ 11 I i // ! I, II ! ! /;r I i I

I ' /� I I ' I 0 . 4 0-+-----4 � - //· �_:_ � ·�- � -- -- - + - --1- j

I / I I I I 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0

ANGLE O F A T T ACK (D EG REES)

( b ) Drag

Fi gure A . 42 - Conc l uded "

9 0 . 0 0 1 1 0 . 0 0

1-z lU

2 . 0 0

1 . 60

1 . 20

----·--· -

-------r---T I

I I I Symbo l ____ _ L_ I El

I t::. '\$' I

I I I I t--------1--I I I I i

AR i I In fi n i te :----1 2 9 6

i 0 . 6 0 +-----��----��--��---- --��--------�------�

u I § 0 . 40+---�� ·�--------+-------�---------��.--

-+------+--�·----+-----i . I

I �----+-- -----·-

-0 . 80+---�--�--�----�--�--4---�--�--��--+---,---� - 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE O F ATTACK

(a ) L i ft

70 . 00

(DEGREES)

9 0 . 0 0

F i gure A . 43- Effect of Aspect Rat i o on Aerodynami c Coefti c i ents of the NACA 4412 Ai rfo i l at RN = 1 . 00 ' x 1 0 •

1 1 0 . 00

2 . 80

.,..-----l---�- I ····-1 ·------l-� ! : I ,�

AR 2 . 00+------

r- I I & � I' I 9 � 1 . 80+----t-----+1-

� I 0 1 � 1 . 20+-------+------�--

0 . 80+------l-----·l-

Infi n i te 1 2 9 6

�--- I I I ! r ---t------+---� 1 / I i I I I --------+---� -·---i l

I 0 . 40+------i-- ·----,-;,L-?"f-------+-----�--------

1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

Fi gure A . 43 - Conc l uded o

70 . 00 (DEGREES)

90 . 00 1 1 0 .. 00

..__ z w H (.) H lL lL w 0 (.J ..__ lL H ...J

2 . 00-r---------r- ____ T _ _ _ l __ _ _ _ ----l 1 Sym,,bo 1 AR I 1 . 60-t--- --+-------+------� ""' I n fi n i te � I 0 12 I

0 . 80

0 . 40

I -v 6

_ _L ___ --t-------

---+--·-----1

-0 . 80+---�---+---.---�---r---;----r---�---r--_,-----r---� - 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

7 0 . 00

(DEGREES)

90 . 0 0

Fi gure A. 44- Effect of Aspect Rat i o on Aerodynami c Coef6i ci ents of the NACA 4409 Ai rfo i l at RN = 0 . 25 ' X 10 .

1 1 0 . 00

1-z w H u H lL lL w 0 u l'J <{ a: 0

1 . 80

1 . 2 0

0 . 80+---

0 . 4 0+----- I ---·-� I

o . oot-�.-��--�--�--t---�-J--�--�--�� - 1 0 . 00 1 0 . 0 0 3 0 . 0 0 5 0 . 00 7 0 . 0 0

( b ) Drag

Fi gure A . 44- Con c l uded .

90 . 00

1-lL H _J

2 . o o�- __ T _ _ ______ l _ _ ________ ------- ----,------ - T--1 . 80+----J- _ __ _ -t- _ - _ ____ _ _ L ----t - ---

1 I Symbo l AR I I ( B I n fi n i te L' 1 . 20+--------ttt��---+------·--·�--- : �2 I ---;

0 . 80

0 . 4 0

I \1 6 I , I . 11-A!---��--+----� ' I I I I I I I l ---��----�---' t I I 1

��-- -----------1�- ---- ----- -�-· ·· · - --··--··+-- -·---1

-0 . 80+---�--�--�--�--�---+--�---4--�----�--�� - 1 0 . 0 0 1 0 . 00 3 0 . 0 0 50 . 0 0

ANGLE OF A TTACK

( a ) L i ft

7 0 . 0 0

(DEGREES) 90 . 00

Fi gu re A . 45- E ffect of As pect Rati o on Aerodynami c Coefti ci ents of the NACA 4409 Ai rfo i l at RN = 0 . 50 x 1 0 •

1 1 0 . 0 0

2 . 8 0,...-----�----------T-

, -l 2 . 40�----+------�-----1--·-----·-

I I 2 . 00+------+----+----

Symbo l

6 1 r- I � 1 . 60+-----+----+---H I lL lL �-�----r-·------11 · I I w 0 � 1 . 2 0+-----+ t ---- --+---- ----1

I I -----i I --�---t---------0 . 8 0 +--------t-------�

0 . 40+---�

I I 1 I I I I --L�

o . oo+-� .. ��-�--�--�--4---�--4---�--�--�--� - 1 0 . 00 1 0 . 00 3 0 . 0 0 50 . 00

ANGLE OF ATTACK

( b ) Drag

70 . 00

(DEGREES)

Fi g u re A . 45- Con c l ude d .

90 . 00 1 1 0 . 00

2 . oo�--- r -- �----T-----·- --------T

I l 1 I I I

-·-·--l 1 . 8 0 +---�t--------f----------t-�-- - � -------r---

1 I ! �Sy�m_bo_l ___ A_R __ __

1 . 2 0+--- I - - �- -�--- � !�fi n i te r-

� I I " i 6

� _., , �� I � 0 . 8 0

_ · I ��r-� 0 . 4 0+---IH;-.1.--+---+---- t-------r I

----------t-- ---

- 0 . 8 0+---�--�--�---+--------�------�--,---�---.---1 - 1 0 . 00 1 0 . 0 0 3 0 . 0 0 5 0 . 00

ANGLE OF ATTACK

(a ) L i ft 7 0 . 00

(DEGREES)

9 0 . 0 0

Fi g ure A . 46- Effect of Aspect Rat i o on Aerodynami c Coefti e i ents of the NACA 4409 Ai rfoi l at RN = 0 . 75 x 1 0 •

1 1 0 . 0 0

2 . 80-r-----r 2 . 4 0+-----1-

2 . 00+-------�-------+

I Symb:..::o_;__l -�A�R __

�- 8.

I n fi n i te 1 2

tj 1 . 80+------+------+-------t----+------+--------1 H LL LL w 0 u � 1 . 20+-----t-----!-------+--

�---:------------

0 . 80+-------�--- 1 ,L /----1----�-------� I / l t/: � ' '

0 . 00��--��--�--�--�--�--��--�--�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

70 . 00 (DEGREES)

90 . 00 1 10 - �00

f-z w H u H lL lL w 0 u f-lL H ...J

2 . 00...-----�

1 60-t-----L- -------+--. I

------.--l---1 l _______ L------1----_j

I I Symbo l AR ' I El 9 i l 0

1 . 20 +-------+----usr.--------t- ·- ------i-------6 --+-------t-· I ! I I I i

0 . 8 0

I I 0 . 40 I ---1-

I I I I i 1-I l

I i I +-. 1 -�-+- � I I

-__,......._.-� 0 . 00+-��---+---------�-------�--------+--------+------�

\ I ----- -+---- �--+---- -----!

-o . so+---�--�--�----�--�--�---r---4----.---+---.---� - 1 0 . 00 10 . 00 30 . 00 50 . 00 70 . 00 90 . 00 1 1 0 . 00 . .

(a ) L i ft

Fi g ure A . 47 - E ffec t of As pect Rat i o on Aerodynami c Coeffi c i ents of the NACA 4409 Ai rfo i l at RN = 1 . 00 x 1 06 .

(!) < a: 0

2 . 8 0�--- -�------� -----,----------�--- - -r - �-l I I I 1 i

2 . 4 0+-----+------1--------T ___ _l _ _ _ _ _ --+1 ----�

I I I , I I ' I

I I I I I 2 . 0 0+----�,-�----�------ I - - - - -----t-----t------ll j ! Symbo 1 AR ! � --

1 . 80

1 . 2 0

1 _l _j _ __ : 1. -- --L---� i 1 I . 1 I I 'I ! 1 I f I ! i I ' I I I _j�--- I ; I I I +------T---t-- - - -r ;---1 ,

I I l f2{ l I I I 0 . 8 0+-------+-- ��-

0 . 4 0+------ �'------�- -- ------- --� 0 . 0 0��+---�--+---�--�--�--�--�--�--��

- 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 00 7 0 . 0 0 ANGLE O F A T T A C K (DEGREES)

( b ) Drag

Fi g ure A . 47 - Conc l uded .

90 . 0 0 1 1 0 . Q,O

I-z w H u H

LL LL w 0 u

I-LL H

2 . oo-.----�T---l---------r-----�r-l-· 1 . 80+--------l:- I ---+-- Sy

�o l

��8 �

0 . 80

0 . 40

I . 0 o . 1 5 8 0 . 1 2 \'l 0 . 09

l -� - -- ------- ------ I I l I I ---�- ----�--r--- ';:---_- ---r 1

I I ' I

I I I ! ! --+--- -�-----·- -------r-···-- - ---·-·-t- · ·-- -\�

-0 . 80+---�--�--�---+--�----�--�--+---�--�---r--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE OF ATTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00

Fi gure A . 48- Effect o f Ai rfo i l Th i ckness on Aerodynami c Coef-fi c i ents ; Aspect Rat i o = a:> , RN = 0 . 25 x 106 .

1 1 0 . 00

1-z w H u H LL 1L w 0 u

(.!) <( a: 0

2 . 8 0

2 . 4 0

2 . 0 0

1 . 60

1 . 20

0 . 80

---� T I

I Symbo l 8 I 0

I 8 --r '\:1

I l ------r-1

t/ c 0 . 18 0 . 15 0 . 12 0 . 09

0 . 40+------+

1 0 . 00 30 . 00 50 . 00 ANGLE O F ATTACK

( b ) Drag

Fi gure A . 48 - Concl uded o

t I I L-------+ I I

--+------ -----�

7 0 . 0 0

(DEGREES)

90 . 00 1 1 0 . 0 0

2 . 00�------�---------.----- -�-T-1 . 60+------

[!) 0 . 18 r 1 l 0 0 . 15 !

1 8 0 . 1 2 I '9 0 . 09

1 . 20+-------��r-��ttT- --� r- I I I i I z . I I ! I g, 0 . 80+----"rl.l-+-�---�- -- ; �-�'et- -------r--� lL I I I I � i I I I � 0 . 4 0

,1 +-- I I I H I I . _j I I ! I . I

0 . 0 0+----m+f----+-----1-------f- -- -l-------1 I I ---T-

-0 . 80+---�--�--�--�r---.---�---.---+---.�--+---.---� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00

ANGLE O F ATTACK

( a ) L i ft

7 0 . 00

(DEGREES)

90 . 00

Fi gure A . 4 9 - Effect of A irfo i l Th i cknes s on Aerodynami c Coef6 fi c i ents ; Aspect Rati o = co , RN = 0 . 50 x 10 •

1 1 0 . 00

2 . 80-r-----------T---l------�T- ---- I I I I

___ l__ . ! I 2 . 40+---- I t-------+----

1 I 2 . 00+---- -+---

Symbo l t/c El 0 . 18

o . 1 s I o . 1 2 r ---0

o . og l

1---l : -� +-- . I I I

e- . I I g 1 . 60 ---t' ---- :', i

)� / j I i

I I � l I I 0

+------+·--- +-- I I � 1 . 20 t'tr--11------·-t-·----+------ti gj I ! I

1 0 . 00 30 . 00 50 . 00 70 . 00 ANGLE OF ATTACK (DEGREES)

( b ) Drag

Fi gure A. 49- Conc l uded .

90 . 00 1 10 . 00

2 . 00...-----

1 . 80-+-----

1 . 20+----

I I -T-. --�---l I I ' I ---+-------+,, --- --- Symb� 1 t/ c

+-------l El 0 . 1 8 i ! o o . 1 5 �� - I 8 0 . 1 2 ----1 \7 0 . 09 ' i I ! � � i I f I l � o . 8 0 --+---------l------r--------L--�

� .11 I I I 11 tJJ 1 : I � 0 . 40+------tftll-----t--------�----t--- I I ��I _J ! [ j I l 1

I l I I I o . 00+-----rlr+f---t- -----------+--- I l------t I I I I I I I

f I ! I -+.4.---- +--

-0 . 80+----r----t----r---+---.---+----.----+------r---f--...-----f - 1 0 . 00 1 0 . 00 3 0 . 00 50 . 00

ANGLE OF ATTACK

( a ) L i ft

70 . 00

(DEGREES)

90 . 00

Fi gure A . 50 - E ffect of Ai rfo i l Th i ckness on Aerodynami c Coef6 fi ci ents ; ; Aspect Rati o = co, RN = 0 . 75 x 1 0 .

1 1 0 . 00

2 . so....---- 1 _____ 1 _ ___ - - - ------- - - - -- - - ------,-- ---� 2 . 40+----t-�- �- ---- �

Symbol - -

-- -� 11, I 0 0 . 18

i I 0 o . 15 2 . 00+----

--t--- --r-�----+-- : � : �! ------1

� I I J i

�u 1 . 80+-----l L--- __ ___jl H I I 1 tt I I I UJ I ! ; 1 . 20 -l ---r--- -----t�-----1- --�

I I . r�--i--0 . 40+-------�-- +-------t----+-----------------

1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

70 . 00 (DEGREES)

90 . 00 1 1 0 . 00

r-z w H

lL lL w 0 u

r-lL H

2 . 0 0-r---------·--�-----l __ _______ l ______ l _ _____ _______ ----- - -, I I I

I I . I

1 . BO+---�-----+�-- ----+--Symbol

. .... t/c -�-1

I I [ I I I I I "' 0 . 18 i I 1 . 2 0+--- ---Hi lff--�------\+-1 ----�---- : � : � � f. - -·· I

1 , l I 0 . 8 0

0 . 4 0

I I I I ·---�----+----: � I I I I I I I I I -+--------t-----··j-----+--------1 I I I

I I I I 0 . 0 0 +---++---+----+- r----+-- --l

I ! I I I I ! I I � 1 . - - - - - - -·-r ·------- ------ .L....--- - ------· --- -- - -- · - - - ----, l I I I

- 0 . 8 0+---�--�--�---+--�--��--�--+---�--�------� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0 (DEGREES)

90 . 0 0

Fi gure A . 5 1- Effect of Ai rfo i l Th i ckne s s on Aerodynami c Coef6 fi c i ents ; Aspect Rati o = co , RN = 1 . 00 x 10 "

1 1 0 . 0 0

2 · 80.....--------l --- _l _ _ __ _ __ l ________ r_ -- --- - -�l 2 . 40+------t---i---------�----- I -----� i 1 Symbo 1 t/ c ·· ) I ! .·. 1 ! c : " \ i G 0 . 18 J . I . I I . 0 0 . 1 5 I 2 . oo-+----r--- . . -·---�----�--- "'

I o . J2 · ---- - 1

� 1 . 60 ! ----� -- ----�-------1-- --L� lL I ! I I tt 1 ' i i 1 8 I ! I I I � 1 . 20+------+----·--j_ _____ _L _________ l, l I a: i . i I I I 0 I I I I !

' I I I , � I 0 . 80+-----r----- 7 ---- ··-- ------- ,-----� ! I 0 . 40+------ r _

__ ---+- ·

0 . 0��--��_j--�---L--�--L---�-J--�� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 70 . 00 90 . 00 1 1 0 . 00

ANGLE O F A T TACK (DEGREES)

( b ) Drag

Fi gure A. 5 1- Conc l ude d o

I-z ll.J H

lL lL w 0 u

I-lL H

1 . 20

0 . 8 0

0 . 4 0

Symbo l 0

t/c 0 . 18 0 . 15 0 . 1 2

Yl 0 . 09

l-�-l i i, I ,

i I ! I r - ·-- - -·------i . i I I i I I

; i ;-��----·-----4

-0 . 8 0+----.--��-------+----.---�--�.---;----.----+--- 1 0 . 0 0 1 0 . 0 0 30 . 0 0 50 . 00

ANGLE OF A T TACK

( a ) L i ft

70 . 0 0 (DEGREES)

90 . 0 0

Fi gure A . 52- Effect of Ai rfo i l Th i ckness on Aerodynami c Coeffi c i ents ; As pect Rat i o = 12 , RN = 0 . 25 x 106 .

1 1 0 . 0 0

1-z w H 1 . 60 u H

lL lL w 0 u

(.!) 1 . 20 <! a: 0

0 . 40+---

1 0 . 00 30 . 00 50 . 00 ANGLE O F ATTACK

( b ) Drag

Fi gu re A . 52- Con c l uded .

70 . 00 (DEGREES)

90 . 00 1 10 . 00

r-z w H u H lL lL w 0 u

r-lL H

1 . 20+---

0 . 80

0 . 40

-0 . 80+---�---+--�----�--�--�--�---4----�--+---�--� - 1 0 . 00 1 0 . 00 30 . 00 50 . 0 0

ANGLE OF ATTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00

Fi gu re A . 53- E ffect of Ai rfo i l Th i ckne s s on Aerodynami c 5oeffi ci ents ; As pect Rat i o = 12 , RN = 0 . 50 x 10 •

1 1 0 . 00

i-z w 1-1 u H t.L t.L w 0 u

t!) <! cr 0

2 . 8 0 ...-----l�---·--r -��T �-- ��- T -1

i I . I I ! I I I I i 2 . 4 0-+--------� + i

! l I i . '·--------1 i

t/c j i ! I I ! I

Symbol 0 . 1 8 [ j

2 . 0 0 +---- ----,1 ------- -t---· ---- ·-t--··� : i l I I I ! l l

0 6 � : � � [ __ __ . - ... __ _j ' I 0 . 09 I I l

1 . 6 0

I ! I I I ! I j i ! 1 i I ·-·+ ------·--t- - - · --· - ----�--- ----- ·----·-r--�:;a==-- ' . =·�--:--1 I I I �� I . ',� I I ' ' I ! I i I i I I ! i i I I I ! ! I

1 . 20 I I I I _j -+ ' I i +----+-- --

I --� --r·---T--·-- - I

I I I -� - -- � L - - �1�--�� i 0 . 8 0 +----

I I I I 0 . 4 0+----· -� ---·-- --- < - - ·--- � +-- � �i�-��-- - �------1 I I I I

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0 9 0 . 0 0

( b ) Drag

Fi gure A . 53 - Concl u ded .

1 1 0 . 0 0

1-z w H u H

LL LL w 0 u

1-LL H _J

2 . 0 0 �---r----� ----- -�- - ---- ---- - ---r --------- - _____ _ _ _ l ___ - - - --l l : ; 1 . I ! ' I ! I ! I I I i : , 1 . B 0 4------r-- ----r------·· · ·-r-- -- ��1- --

t/c l---1

I ' ! l l B 0 . 18 I l 1 . 2 0-+----�--�- k- -- --L- _ : � : :: �-- - i

1 I \9 o . 0 9 ! 0 . 8 0

0 . 4 0

I , i ! I I

! I I - ---�-----�----,--, I I I I I i � ' ' I l ; I ! I -�, I 1!: L I I I 1 --, ----·-t - ----t----t----t· i 0 . 0 0+-----�-�+-----·--r----

. ---�-- ·i'-· ·- � ------�

·,. I : I i I I I l / I j ! J I ' , , I i i I i -t---- - - ·t -- -- - -- ··· t· .. - - · - ·-- ··· · t·--·-----�----·--

- 0 . 80 +---�---+---�----�--�--�--�---4----�--+---�--� 1 1 0 . 0 0 - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 0 0

ANGLE OF A TTACK

( a ) L i ft

70 . 0 0 (DEGREES)

90 . 0 0

Fi gure A . 54- E ffect of Ai rfo i l Thi ckness on Aerodynami c Coeffi c i ents ; As pect Rati o = 12 , RN = 0 . 75 x 1 06 .

f-z w H u H

I.L I.L w 0 u

(!) <t a: 0

2 . 8 0 ...--- -----�- -- -----·-r- - - -· � ·-· -·1---.. - -----·- - - · · - - --- - -·- - .. . . ---1 I I .

2 . 4 0 �--I I j

I I I i ! I El 0 . 18 I ! I I I 0 0 . 1 5 l I

2 . 0 0 �---·l -- --- ----r---�·---r--- : � : �! �- --� I I ! I i

1 . 6 0

1 . 20

'I I i ' I 1 i I I ! i I i I

-t---------1· --�- - - ---r-------------r-----------+------�

I I I � I I j. I I /f i I -+----------- ,----t -t-:- . ·-t,' --�---� ---� I I l I . __]_ I I I 0 . 80+------+�-- - -+-----1--� -� I I .

I I I I

0 . 40+-------t·---·-M--1-Ir-lr---I 1 I

--+-. ------1--·------+---·-1 I I I �

1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

Fi gure A . 54 - Con c l uded .

70 . 0 0

(DEGREES)

9 0 . 0 0

1 1 0 . 0 0

2 . 001 -----l -------- ---- _______ l _ _ _______ _ _ __ _ _ - - 1 --------- -- , - - - ------·r ·------,

! ! I I ! I I I I i ! I

1 80 - -+ - - ·--- - -+-----------J_ ___ _ ___ I L------� • I t I . I I 1 ! Symbol t/c ·

r I l I ' i I i I I 0

1 20+------J _ _ _ _ _j__ ___ 8 0 . 1 2 ,__1 -- ---� . i l I

0 . 18 0 . 1 5

l I r- I I i z . : I I � 0 . 80+---- r------t�------- I ----- �- ---t-�- --l lli I ! 1 I 0 I I ' I I I u l l ! ! I I

� 0 . 4 0+-------- -1--------1-----J-------�---------1---�� _J ! : I 1 I 1· i I . I I . . I 0 . 0 0+---H--____,'------------t· ,---------�-----------·--r-· ·-·-------t

! I 'i I l ! I I ' i 1 i i ' i I I I I I ' I i I ' +m--- - ··- --�------ .. ------- --- - -.. +- - .--- - - - - - -------t- - ---- · - · - - ·-- - i--- - ------ .. -- - - · - f- · - ·· - " " ----· _ ____j

I I [ i I I I

-0 . 80+---�---+--��--+----r---4----.---�-------1----.---� - 1 0 . 00 1 0 . 00 30 . 00 50 . 00 ANGLE OF ATTACK

( a ) L i ft

70 . 00 (DEGREES)

90 . 00

Fi gure A . 55 - Effect of Ai rfo i l Th i ckne s s on Aerodynami c Coeffi ci ents ; Aspect Rati o = 1 2 , RN = 1 . 00': x 106 .

1 1 0 . 00

f-z w H u H

lL lL w 0 u

(.!) <! a: 0

2 . 8o�--l r -- - - --�r-- --- - 1-- -- 1 - - - - -l .,. l Jl I I ! I I I I i

2 . 4 0-+-------r-----r --�-- i --Symbo l

t/c ·- r·-- - -- l

I I I El 0 . 18 i I I I I i l 0 0 . 1 5 I _J

2 . 00+-----,-- �-------:·- 8 0 . 1 2 �----- !

l I I I ! 1 . 60

1 . 20

i I I ! i ----t---��-t------�------j ---: I l 1' i i I I I

I i I I I I ----T-· ---·--+- ---- --------;---�------i·----1 I . I I I I I I I I . ! I I I I I 'I l I f I 0 . 80-+---------.-�� ---�l-- r---- --- - -r---1

- I i i 0 . 4 0+---�---+------ -·-t--

1 0 . 00 3 0 . 00 5 0 . 00 ANGLE O F ATTACK

( b ) Drag

I I -------- ·-----�

7 0 . 0 0 (DEGREES)

90 . 00

1 1 0 � 0 0

1-z w H u H I.L lL w 0 u

1-lL I-I ....J

2 . 0 0 1 r- - - -T - - - ---- - -1--------l� --------l-- ------� l ! I ' I i ' I : : I I I I i • r i ! i I I I I ; I · I

1 . 6 0 +---------�---- --------t---------t----· I 1" --- - - ----� · I i Symbo 1 t/ c · I '

I I I . I 1 . o o . 18 i i

1 . 2 0+----- - -�--

0 0 . 1 5 i 8 0 . 1 2 f-- - __ _ _ _ _ _ ___J I

0 . 8 0

0 . 4 0

'V 0 . 09

i ---<�- . :---- -

. . -- --- r-- . -----�� I -�- i I' I ' - I I

I ' I ' II I ! I I I ' ---:-- ---------�----t--�--� -�:- i -- - - -� II i I ! �\ i I : I I -.��\�1 -

+--c{H----- ·- _ _L ______ l_ ______ _j_ ___ _ _ _ _ l ___ __ �-- ----i I I I ! I \ \ ! I i I l \ \\ I I ! I I I �, I I I i I I � ' ' I ! : · l . ! I \ I' j f ' ' 1 ,\ \ I I ! i I ' \\

- o . 4 .... m-----r-·- ··-···· �-��---- -r·--·-··· ··· · ··r - ·· · ·- -r - --,

I I' ' I' i - 0 . 8 0 +--�---4----�--�- -�---+----.--�----.---�---.----4 - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES) 9 0 . 0 0

Fi gu re A . 56- E ffect of Ai rfo i 1 Th i ckness on Aerodynami c6coef

fi ci ents ; As pect Rat i o = 9 , RN = 0 . 25 x 10 •

1 r.: n

1 1 0 . 0 0

f-z w H (.) H LL LL w 0 (.) (!) 4' a: 0

2 . 8 0 -r--- �-- �-�-- ��-1-�- - -l- -� --1- -l I i ! 1l !

2 . 4 0+---- I --�-

---- ---�-- -- Symbol tjc - -

----� I I I

I : i !

I ! l : � : �: i +-------L- ------ -J-- .- -�� ----- �-----1 �------- I

2 . o o , I I e:. o . 1 2 I I '

1 . 6 0

1 . 2 0

0 . 09 i : I I I j i I I ! +-----·-- ·-- t�-------1-�-u-- - .

� - t --)V''� � ! � � : Rl ---� $ . , "+ I I ' I � · i i , 1 ·ttJ +------l----�- ---- -J ___ ,�{�l ______ ___ _ L __ ____ J I : ! ./ I I I i ,

! I l 1 -�� - I I

0 . 8 0 +------·--;�---------,-- -- ----- -----�-r-�-----___j

I I i I I I i I I I I f 1 I I 0 . 4 0 -+------- --+----- - ��------------� -- --� ---� -+- - � - --- � ---1------ -----�

i I i I I ��_J_� I I I 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0

( b ) Drag

Fi gure A . 56 � Conc l uded o

9 0 . 0 0 1 1 0 . 0 0

1-z w H

lL lL w 0 u

1-lL H

1 . 2 0 +---

0 . 8 0

0 . 4 0

0 . 1 5 0 . 12 ------ --� o . o9 1 I I I

I i I I I I

�---4----- -- -------r----- .. � I r i I

I I I · I 1 J I

�--- ·-·--"---�� - �--

, I I 1 I

o . o o �-1-/l- ---t-----1------�-------1 I 1 r

I 'II I I I I

4--M----+----j______ --·- ······-----' I

- 0 . 80+---�---+--�----�--�--4---�---+--�----�--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

(a ) L i ft

7 0 . 0 0

(DEGREES)

9 0 . 0 0

Fi gure · A . 57- Effect of Ai rfo i l Th i cknes s on Aerodynam i c6Coeffi c i ents ; As pect Rat i o = 9 , RN = 0 . 50 i x 1 0 •

1 1 0 . 0 0

2 . s o� l---- r -T---- ------ - -----l----- --1 2 . 40+-------� ------L----

-� 1,--- __ J

I 1 Symbo l t/c : I ! I I . , ! I I El 0 . 18 I t I f

2 . 00+-----t-·-----L-- --�-- : � : �� ----� I 'l 0 . 09 I I I I �u 1 . 60+------l- 1 ----�-------, -- _L __ �I . --+- l l r I li 1 I ! 1 . 20 -j- -- --- --t-----L� 1 § I I I

0 . 80+---

0 . 4 0-1-----

1 0 . 00

- -� I -----1------·--j _______ _ I --,

30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

Fi gure A . 57- Conc l ude d .

70 . 00 (DEGREES)

90 . 00 1 10 . 00

I-z w H

lL lL w 0 CJ

I-lL H _J

2 . o o�-- - -- -- - T · --- - ·--··- ·- - --- · ---- � - -- - · - - · - - - - [ . ··· ·-· · ·· · - · -- · · j - . 1 .. - -----·! l I I I I I

1 . S o +--- -- l - -- - 1- - · ··· _ _ ] _ _ _ I 1 -· - - �

i ; I Symbo l t/ c [ : t i 1 -=--Q---o-. 1-s-l I I t 0 0 . 1 5 I

1 . 2 0 4------ -- l -·--rJ\fi __ _ _ 1 . . . . _ _

.. r- _ : � : �: 1 ..... .

_ _ _ 1 , i •11 i i

0 . 80

0 . 4 0

\ ! 1,1 I j ' I ' n�1:�t:� - · ·· · + · · · · ·· · - - + ·· - -� ; I : l I �

' i �· i 1. i I I I - + - - �- - -� · · ····· - - +- - - - +-- , _ _ , _ - --� II il1 I I I I I I i '

t I i I I ! 0 . 0 0 +--llk----·- t - -- -- -· i- � - - -- r - --- I -- - --T - �-l

I I I I I ' I I ! I 1 I \, I +W----�--- ·-·-! · · ----- ·- -- - -·- . - -1 · -------·-- - -- ·-- - 1-- - - - · - - ·-· -···--- - · - -· +· - · · - - -· - .. ..... __ J._ - - - . · ----4!1 i I I t I . I l I I

- 0 . 80+---��-+----r---+----r---+----.---+----.----+----.---4 - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

9 0 . 0 0

Fi gure A . 58- Effect of Ai rfo i l Th i ckness on Aerodynami c6Coeffi ci ents ; As pect Rat i o = 9 , RN = 0 . 75 x 10 •

1 1 0 . 0 0

1-z w H u H

ll... lL w 0 u

(.!) <( a: 0

2 . sol--- T--- - - T - -- - r - - - - - - r · ·· · · --- · · · · - � -

� 1 j ( i 1 : i I i I I : I ! ' i '�� 2 . 40�----_J____ _______ L-- -- ---- -- - --------l------- 1

+-.-:--

Symbo l 8 0

t/c I 2 . oo�-----·---�--- - - - - --------;-------------·-- - - -+---- - - - --- - 8

0 . 18

0 . 15

0 . 1 2

0 . 09 ! i

1 . so-+--------· --r------------r----- ----r--- ------ --- --t------------- - - -- f--- ---

-----1

: 1 I I )

; � ; f

! ! Yr �� i ' I ! I 1 . 20+---·--------- ·t-·-------r------ --- --1-------- - --�------i, i i r '

I i ! I . I 1 � I 1 I !

• f I ; l l ! ' I I o . 80-t------·T-------r---------

, � --�---------L--- --- ---------1----------; 1 I I

0 . 4 0 ,-- -----1

1 0 . 00

l ' i l I I I I ' ! I I ' I ' I -- --------------- - -1 --�·�-- ---- ----- -- - - ---- - - � - - -

30 . 00 50 . 00 ANGLE OF ATTACK

( b ) Drag

70 . 00 (DEGREES)

F i gure A . 58 - Conc l uded .

90 . 00 1 1 0 . 00

LU r -1 0 H lL l.hlio w 0 u ILL H ..J

2 . oor---�r- -- -"---- · -----:- - - - - - ---- --- -r - - -

: I ; [ ! \ I ' ; I ! i ; j' i : ' ' 1 . 6 0 ----------------,.-------�-�- ---� ---------- · ----�--- - -- --- --+-- ----

:1.. 20 �----- -- - - '�-··---- - - � -1

o . e o -------- ---- -

0 . 4 0

""� ·· ---- -- -- --- �-1---- - �-------, I I

Symbo l t/ c 0 0 . 18 0 0 . 1 5 6 0 . 12

0 . 09

i i - - - _ ; ! ' i I I

i � -�- --i

--0 . 8 0 +---�----�----r---�----�---+----�---��----�----�--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 7 0 . 0 0 9 0 . 0 0

ANGLE O F ATTACK (DEGREES) ( a ) L i ft

Fi gure A . 59- Effect of Ai rfo i l Th i ckness on Aerodynami c6Coeffi c i ents ; As pect Rat i o = 9 , RN = 1 . 00 x 1 0 •

1 1 0 . 0 0

I I _a

2 . 8 0 -r-------

0 0 8 0 +-------- -- --,_ ___ _______ _ _ - - -,- - ---

0 . 4 0 +--

1 0 . 0 0

-�--··- - - - -- � � - -

3 0 . 0 0

5 0 . 0 0

ANGLE OF A TTACK

( b ) Drag

Figure A . 59 - Concl ude d .

Symbo l t/ c EJ 0 . 18

0 . 15

0 . 1 2 \;7 0 . 09

r - - • - - - - - �·--·--

--_______ J r I

7 0 . 0 0 9 0 . 0 0 1 1 0 . 0 0

(DEGREES)

ILL H ..J

2 . 00�-

1 . 60+----

1 . 20t-- - - ... j I . i

0 . 801-- - - ---1

j 0 . 40t----

--+ --:

i -- ----- - - ----t - -- - -!

i I I - - · �� -- - - � - �- - - f- --·-i ' i i i I

i I - - - ---- --- -1 Symbo l t/c i

0 . 18

0 . 15

0 . 1 2 '

__ _ I I

\:1 0 . 09

r-- · - ---- - � . --- - - 4 - � - - - - -- - ---- - - �---t t ! i

'-'k "-f --- -- ,- . __ J __ _ !

i I ' I l ----- ---- - - -1- - ---- --------�

' l --�-�-·�-- --- - - _ _ J __ ! --- ---- ----- - - - ---�-- - - --- ______ _ , ---- ---�

-0 . 4 --- __ , __ �� - --�-� -------- ---- --- ---'

-0 . 80+---�----4---�r---�----�----+----�---+----,-- -�--�----� - 10 . 00 1 0 . 00 30 . 00 50 . 00 70 . 00 90 . 00

A N G L E OF ATTACK (DEGREES)

( a ) L i ft

Fi g ure A . 60- Effect of Ai rfo i 1 Thi ckness on �erody,nami c6coeffi c i ents ; Aspect Rat i o = 6 , RN - 0 . 25 : x 10 •

1 10 . 00

1-z w H u H

LL LL w 0 u

t!l <! a: 0

2 . 4 0 +---

- · l ·

r I I I I

_ _ _ L Symbol t/ c

El 0 . 18

0 0 . 1 5

2 . 0 0 +-- -· - --- --· · - -- · -' - - � - ---· -· · · - - -�· - ! - -- �-- - - �- 0 . 1 2

0 . 09

1 . 6 0 -- - 1 ·- -- - - · - - · - - · ·

1 . 2 0

i 1 0 . 8 0 ---- . . - ·---+ - . . . . . --------! j ' 0 . 4 0�-� - ·+

. ·· 1 ·· --- ·-·- . - ·-- - - · - - - - i

I I i i l I 1 -t---- ---�-----· -� --- ---r-- - - - - - - -------J - - - - ---- --- -----1

I I ! I I

l ; ! I I I I

- -- --- L -·-·-- --- ·- ·- ---L __ __ __ -- - ---. --..!---·--- - --- � 1 1 r 1 . i l I

I! I ��-�� --��--4---��--�-4--�� 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE OF ATTACK

( b ) Drag

7 0 . 0 0

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

I-z w H u H I.L I.L w 0 u I-I.L H _J

2 . 00 -r----- -- - -��

1 . 60+----·--- - - - -- -- - -- - -

1 . 20

0 . 80

0 . 4 0

. . -- - J . . . --- . . -- - . . . - - . -· . . I

-·-·--- - - . - ---- - -t - - -- . -- -----! ! I

' - - '

Symbol

0 . 18

0 . 15

0 . 12

0 . 09

I I ! �--- - - - --------� I ! i . i i

l --- · - - ·- -- --�

i ! --- �--- - ---r- ------- - -- -- --- - 1 - - - - - ------ � - _ _ ,_ . ---------- . --� _ _ _ _ _ _j !

! l l l '::fPJ"'---·--·- -- -- - - . . -- - - · -· - - - - -----i ' -- --- --- ------ --- +- - - - - ---- -- - - --- -1- - -- -- -

- o . a o��--�, �� - 1 0 . 00 1 0 . 0 0 3 0 . 0 0 5 0 . 0 0 70 . 00 90 . 00 1 1 0 . 00

ANGLE O F A TTACK (DEGREES)

( a ) L i ft

Fi g ure A . 6 1 - E ffect of A i rfo i l Th i c kness on Aerodynami (! Coeffi c i en ts ; As pect Rati o = 6 , RN = 0 . 50 x 1 06 .

(.!) � cr 0

2 . 8 0

2 . 4 0

-r -- - - - - -- - . -

I ! ! i l - - ·-r· - - - . i !

- ----- · ·-··· · -·- - ·-r ·--·· - · · -- -- - --- 1-----1 I i I

I I I l

Symbo l

l ! . _ __ __ _j

0 . 18

0 . 1 5 i 2 . 0 0 +------ --- · -·-- -- ------- ··-/--- ·----· 6 0 . 12 I - -- �-� i------- - I

1 . 8 0+----

I l I I '\7 I I

0 . 09 :

; i . I ' i ! I . - � ---- --------· ·--�+- ---�- __ _ _ _ .., __ �--t·----- --�---�--- - --��- --..- --·- ---- -- -i- ·---�-- ------1

l I I '

1 . 2 0 +------ -----1--- ------- ---,-----···· ·--·---�----- --- - -----

I -- - - - - -·-· - · -·-j- . - ---- - ----· -·-----1

I ' ' I : j ! I , , I 0 . 8 0+---------t- ------------T---------

l j j j !

I I I I I 1 ---�- ----------+ - ----------1

i I l I i i I I I I I 0 . 4 0 +------- ---- -i---------Yf.-H------- --+- ----------+-- -- - ·---·---- --- - ---�

li I ! i I I

0 . 0 0�--��---L--�--J---�--��-J--�--� - 1 0 . 0 0 1 0 . 0 0 3 0 . 0 0 50 . 0 0

ANGLE OF ATTACK

( b ) Drag

7 0 . 0 0

(DEGREES)

9 0 . 0 0 1 1 0 . 0 0

1-z w H

lL lL w 0 (.J

I-lL H

2 . 0 0�--

1 . 60 I

1 . 2 0

0 . 804-----

0 . 4 0+----·

i i I ·-- . -- · - ... . - - -� ---- - - ---

I i i I

- - - .. . -- - - - - --- +-·- -------

1 I ' l l i

Symbol

- -- - ---- --- - -r · ·-- ---l I !

0 . 18

0 . 15

0 . 1 2

0 . 09

i ---- - - · -----1

' · ··· - - - ----� I !

j ! I ��=-��-;-·=.-·------ --r----------;·-· I !

i j ! \ i · ( I l i i ; I

I i I ! i i --t- ---- - -- - · - ·- · · 1------ --- ·r- · - - -----t-·- --- -----t---- --·-- ---1

; I I I ! I i I i \ I ' ! : ! I : ! i I I ; i f i l ! t 1 1 1 ;

0 . 0 0 -t--NJr-----1-. ---- - ------,-- . -----· --- --+----·-·

·-··--�-- --- -------i -- --------1 ! i I ; : 'II I I ! !

-0 . 4 0�---· - - - - -·-l - ··- ------1- -- · · · - -- --� ----- -- - � - - J . - -� I ' I l I I I 1

-o . eo+---�---+---r---4----r--�---.---4----.--��--.---� - 1 0 . 00 1 0 . 0 0 3 0 . 00 50 . 00

ANGLE O F ATTACK

( a ) L i ft

7 0 . 0 0

(DEGREES)

90 . 00

Fi g ure A . 62- Effect o f Ai rfo i l Th i ckness on Aerodynami c Coeffi c i ents ; As pect Rat i o = 6 , RN = 0 . 75 x 106 .

1 1 0 . 00

t-z w H u H lL lL w 0 u

(.!) <! rr 0

2 . e o � -· - - � · �·· ···· - - ····· r· �- · . . .. ... .. · · · - . .. ·· · ···· ·T - - · - · . - -1 -- - · · · ·· -� : ! I ! ! !

2 . 4 0

I ! : ! I ! I : I I ! :

--- -- --�-- - -·· ·--- ·- --t------- · -- _j________ ! - - �--- · " ··--- - ·---� ! l I i ! 1 : 1. Symbol t/c I i I I ' I l I I i ' 0 0 . 18

2 . o o �-�- · � - --i- -·- - - --l- -�- : � : :� �- ·- �_j

1 . 6 0

1 . 20

I I i 9 0 . 09 I I I ' ' ; ! II : I : I ! t , ' i ! f : ! ' I 1 i 1 f ) ----- ________

I; ------·------t--�1 ---- - -- --- ---t-----------t-- - ------�+-------------1

1 I ! I I I I i f J ! I \ i l I ! ; ! , I l 1 1 i l I � -+-------- - 1 - ----------+·--·-· ·----- ·---+-· ---- __ _ _: __ _

i I I I I . i I l I I i I I I I I . · I I

0 . 8 0 -+----�-� - r-···�- �-- -------��-�-·-T l I ; I i I I ' I , I r :

0 . 4 0 4--------�---------- --------1· ---- -------+------------ ----- --l-· I I I I

1 0 . 0 0 3 0 . 0 0 5 0 . 0 0

ANGLE O F ATTACK

( b ) Dra g

F i gure A . 62- Concl ude d .

7 0 . 0 0

(DEGREES)

90 . 0 0 1 1 0 . 0 0

2 . o o ..----------r� - -�r · · - r� - � r -- · - - l �-- - -, i : I I I ! I i ! I I I I ' ! I I !

1 . 60+-------+ - ----------t----- ------r--------__j_----------r----- -- - I

� I I Symbol t/ c !

1 . 20

I / : j i I t::� o o 18 1 1 l i o o o 1 5 I I ------r' ---- ---- 8 '\;.7 O o 09

._ i I I i

z ' i i -l' w ' I · � 0 0 8 0 --.110'---"9=�-::::ill��--------l------+-� �-t::t--t:t--�,____� I t �

+--------Itt �l----�----� -----l' ____ 1 _ J I t 0 0 4 0 ' ' H I l I ) I _J I : I' I i ! I

0 0 0 0+---�-� -l- -� i -·-----,--------1-------- � - �� i I I I I I _____ L-._ _ _ _ t--··-1-- - -�� -t�- --- -t --

l -0 . 80+---�---r--�--��--�--�--�--�--��--+---�--�

- 1 0 . 00 1 0 . 00 3 0 . 00 5 0 . 00

ANGLE OF ATTACK

( a ) L i ft

70 . 00

(DEGREES)

80 . 0 0

Fi gure A . 63 - E ffect of A i r fo i l Th i ckness on Aerodynami c6

Coe ffi ci en ts ; As pect Rat i o = 6 , RN = l . OO ·x 1 0 •

1 1 0 . 00

I-z w H u H lL lL w 0 u

(.!) � a: 0

2 . 80 - , · · ··· ·· · ···· ····· · ·· 1 · ······ ·· · · � ····· -- - r --� - ····· ·· 1 I : j I ; !

2 . 40+----____; __ __ j __ _______ _______ _ �- --- --- ···-�----- - �- - -----� I J i Symbo 1 t/ c l i ll 1 I I ! i i G 0 . 18 I 2 . 00+----· - -·+- · - -- -l · . + -· : �: �! 1· --·l

' I I ;

1 . 60

1 . 20

; i 'j, 1' t ! t j � : +-------�------ -------4--- -----------t- ---------�-------L _ _ _ _ __ ·J

I l i I ' I i 1, I I i I I I : I I I �T-----.0 ·· -+·· �--- - t------ ! -------�---1 . I I i ! 1

0 . 80-t--------- --- ···l------ r---t-- ·--··-�--� I l I I I

0 . 40+---I _

--·- -t------- - --� --- 1_____ I

1 0 . 0 0 30 . 00 50 .. 0 0 70 . 00 90 . 00 1 1 0 . 00 ANGLE O F ATTACK ( DEGREES )

( b ) Drag

Fi g u re A . 63� Concl u ded .

,.; STR-2559 5i::�l �� -------------------------------------------------------------------------

APPENDIX B

WAKE RAKE DRAG ESTIMATION

�vake rake drag measurements are given for t he four t wo-dimensional blades ( Figures B. 1 through B.4) . The angle of at tack range is restric ted to -10° to 1 2° . This is done because the moment um defect met hod of estimating drag is not amenable to the highly separated flow regimes present beyond a t 1 1 • These measurements are useful in estima ting end plate drag using t he pro�e�ure given below.

A t pre-stall angles of at tack, the end plate drag is the difference bet ween force balance drag and the wake survey drag. The end plate drag consists of tare and interference drag. It depends upon the lif t coeff icient as well as airfoil sec tion shape. In higher angle of at tack regimes, t he end plate drag is estimated by linearly extrapolating the (low lift coefficient ) end plate drag curve. The extrapola tion gives a reasonable estimate because at high angles of at tack, t he sec tion drag is the dominant factor in the force balance measurement.

0 . 0 7 0 -�1 j - -- -- - ---- -- -,

"' �_A 0 . 060 � -

0 . 0 50

� 0 . 0 4 0

0 . 03 0

0 . 0 2 0

0 . 0 1 0

I - . ·- ·---:

0 I � I i

- _ . ! .

Symbo l

I .8 \:1

I , _ __

i - �

Gl 0 9:J � 0 t;:;. I "'

RN ( x

0 . 25

0 . 50

0 . 75

1 . 00

· 8 8 0 A "'

0 'o/:

106 ) I

-- . -

I I I \ I ---� �- - -

� JJ

' -� - --· ------; I 0

- - ----

�- -- -

. _ ___ j

0 . 0 0 0 +---�----�--�---��--�---4----�---+-----�--41�--�--� - 12 . 0 0 0 -8 . 0 0 0 - 4 . 0 0 0 0 . 0 0 0 4 . 0 0 0 8 . 0 0 0

Fi gu re B o 1 - Wa ke Rake Drag Coeffi c i ent of the NACA 4418 A i rfo i l (Aspect Rat i o = co ) .

1 2 . 0 0 0

0 . 1 4 0 ...----

0 . 1 2 0 s ·

T I - I ! . . , I

j 0 Symbo l

o . 1 o o I - � i - � - . -r-- . i I : I .

0 . 0 8 0 +--

I o . osof--------- - � - - --- - -- - -+ - - - - - -- - _ ,_ __ _ -

0 . 0 4 0 - - - - - - - - - � -� �--- -- -- - -- - - -- · - - ---- - -

0 . 0 2 0 +---

' ' ' ' I

- -� --- f-- - - - - --- -- - - · - - 1- - - � -- - - - - --

�. i '

' ' , __ I

0 !!::.

0 . 50

0 . 75

-- l - --

I � � 0 . 0 0 0 �---.------+----r--+-1 ----.--+--1 ----.-- � --L

- 1 2 . 0 0 0 - 8 . 0 0 0 - 4 . 0 0 0 0 . 0 0 0

ANGLE OF A TT AC K

4 . 0 0 0

( D EG R EE S )

8 . 0 0 0

Fi gure 8 . 2! - Wa ke Rake Drag Coeffi c i ent o f the NACA 4415 Ai rfo i l ' (Aspect Rat i o = co ) .

- ------· !

1 2 . 0 0 0

0 . 1 4 0 ...----

0 . 1 2 0 +-----=0

0 . 1 0 0 +----

0 . 080

0 . 02 0

0 . 000 - 1 2 . 00 0

-- [ - - .

Symbol

-- -.4-.----- . .. . --· -'

- � - - - - - - - - - - --- - - -- ·--

� - - --- - . - - - -

· - � r I '

I 1!1 •19

-8 . 000 - 4 . 000 0 . 000

A N G L E O F A TT A C K

0 . 50

o . 75 .

1 . 00

--- -- - - --[ - - - -· � - · ---i

' · · - -- - --- - - - ---l --- - -- - --- -- ----- - - - i- - -- -- - - - - - ---

. -- - -

� i I

4 . 00 0

(DEGREES)

- - --- - - - - --· - --- - -· - --- ___ ___J � 'iV i

I I I 8 . 00 0 1 2 . 00 0

Fi gure B . 3; - Wa ke Rake Drag Coeffi c i ent of t h e NACA 4 4 1 2 A i rfo i l (Aspect Rat i o = co L

0 . 1 4 0 1--- - r '

0 . 1 2 0 +-- --- - -- -- - - - · -

8 0 . 1 0 0 +-------·- ·- · · - -:- -· - - - -

0 . 0 8 0 +---

Symbol [:] 0 . 50 0 8

0 . 75

0 . 0 60 +---- -- - - -� - - L - - -

0 . 0 4 0 ' '

-�-----� -� - � �- - - - - --·--- � � -- - -- � - ------�-�---- -t-0 -

- ---- - - +

- · - - --- -- � I I ' i

' -- - - ----

- ·· - �- - --- -- - - -- _ _ _ _ ___ ., '

[J 0 . 0 2 0 - - --1-- --- - -- - l -- -- - - - -- ---i

I D 0i ;

o . o o o �� e�8�� -� - 1 2 . 0 0 0 - 8 . 0 0 0 - 4 . 0 0 0 0 . 0 0 0 4 . 0 0 0

A N G L E O F ATTACK ( D E G R E E S )

Fi gure B . 4, - Wake Rake Dr�g Coeffi c i ent of the NACA 4409 ·Ai rfo i l (Aspect Rat i o = co ) .

8 . 0 0 0 1 2 . 0 0 0

Document Control j 1 . S E A l Report No. 1 2. NTIS Accession No.

Page LsERI/STR-?1 7 - 2559 4. Title a n d Subtit le

Post Sta l l Wi nd Tunne l Data for NACA 44XX Seri es Ai rfo i l Secti o n s

7 . Author(s)

C . Os towari , D . Na i k 9. Performing Organizatio n Name and Address

Aeros pace Eng i neeri ng Department Texas A&M Un i vers i ty . Col l ege Stati o n , Texas 77843 -31 41

1 2 . Sponsori n g Organization Name a n d Address

Rockwel l I n ternat iona l Corporati on Rocky Fl ats P l a n t Wi nd Enerqy Research Cente r Gol dPn Col orado 80402-0464 15 . Supplementary Notes

Techn i cal Monito r · J Tana l er 16. Abstract ( L i m i t: 200 words)

3. Recipient's Accession No.

5. Publ ication Date

January 1 9 8 5

8 . Performing Organization Rept. No.

10. Project/Task/Work Unit No.

4807 20 1 1 . Contract (C) or Grant (G) No.

(C) DE-AC04-76DP03 533 (G)

13 . Type of Report & Period Covered

Techn i ca l Report 1 4.

W i nd turb i n e b l ades operate over a wi de ang l e of attach ranq e . Un l i ke a i rcraft , a wi nd turb i ne ' s ang l e of attach range extends deep i nto sta l l where the threed imens i ona l performance characteri s ti c s of a i rfo i l s are not general l y known . Peak Power pred i ct i ons u pon wh i ch w i nd turb i n e components are s i zed depend on a qood understand i ng of a b l ade ' s pos t- s ta l l characteri st i c s . The purpose of th i s w i n d tunnel study i s to characteri ze the performance characteri st i cs of a b l ade i n sta l l a s a functi on of i ts aspect rat i o , a i rfo i l th i cknes s , and Reynol ds number . Th i s report documents resu l ts of the wi nd tunnel 1 nvest i gati on of constant chord b l ades hav i ng four aspect rat i os , wi th NACA 44XX seri es a i rfo i l sect i ons , at angl es of attack rangi ng from - 1 0° to 1 1 0 ° . Tests were conducted at Raynol ds number rang i ng from 0 . 25 x 1 06 to 1 . 0 x 1 06 . The th i c kness rat i os s tu d i ed were 0 . 1 8 , 0 . 1 5 , 0 . 1 2 , and 0 . 09 . The a spect rat i os were 6 , 9 , 1 2 and i nfi n i ty . Resu l ts of force and pi tc h i ng momen t measu rements over the ang l e of attack range for a l l comb i nat i ons of Reynol ds numbers , thi cknes s . and aspect rati o s , and the effects of bounda ry l ayer tri ppi ng are presented .

1 7. Document Analysis

a. Descri ptors Aerodynamic s ; Air foil s ; Boundary Layer s ; Data ; Performance ;

Reynolds Numb e r ; Turbine Blades ; Wind Power ; \vind Tunnel s ; Wind Turbines

b. Identifiers/Open-Ended Terms

c. UC Categories

1 8. Avai labi l i ty Statement

Nati ona l Tech n i ca l I nformat i on Serv i ce U . S . Department of Commerce 5285 Port Royal Road Spri ngfi e l d , V i rg i n i a 221 61

Form No. 0069 (3·25-82)

1 9. No. of Pages

20. Price

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