Mensa XE (Extra Efficiency) High Efficiency Family Airplane

Mensa XE Mensa XE (Extra Efficiency)(Extra Efficiency)

High Efficiency Family AirplaneHigh Efficiency Family Airplane

Michael Duffy

Due: December 11th, 2007

Georgia Tech – AE 6343 Aircraft Design I, Project 2

Presented to: Prof. Dimitri N. MavrisHonor Code Statement: “I the above signed certify that I have abided by the honor code of the Georgia Institute of Technology and followed the collaboration guidelines as specified in the project description for this assignment."

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IntroductionIntroduction

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Introduction - RequirementsIntroduction - Requirements

Mensa XE is a High Efficiency Family Airplane A four seat, low-cost, high efficiency family aircraft. 20 year entry into service.

Design Mission: Payload: 2+2 Pax + baggage (400 + 240 + 160 lbs = 800 lbs total) Block Fuel Burn: > 30 miles per gallon Range: 700 miles (608.3 nm) Loiter: 45 minutes, end of mission

Performance Requirements: Cruise Speed: > 200 mph (174 knots) TOFL: 3000 ft, over 50 ft obstacle V_stall < 61 kts Stall V_TO >= 1.1 V_stall Takeoff V_CL >= 1.2 V_stall Climb V_A >= 1.3 V_stall Approach V_TD >= 1.15 V_stall Touchdown Climb: 300 fpm @SLS

Miscellaneous Requirements: Glass cockpit flight instruments VOR/ILS/GPS navigation w/on-board map Limited auto-pilot features (altitude and heading hold) Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)

Source (1)

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Introduction – Mensa XEIntroduction – Mensa XE

Range = 700 miles

Cruise = 200 mph

Fuel Consumption = 39.7 mpg

Engine = 250 HP

V_stall = 51 knots

Take off distance = 2,227 ft

Landing distance = 2,817 ft

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Conceptual Sizing and Synthesis Conceptual Sizing and Synthesis –– 33--ViewView

Graphical Model (3-view) FINAL DESIGN

38’

24’

6.5’ – 6 bladed

Wing Area = 138 ft.sq.

FINAL FLOPS SIZING AND PERFORMANCE RESULTS

OPERATING WEIGHT EMPTY 1506.7 LB

PAYLOAD 800.0 LB

MAXIMUM FUEL 136.6 LB

GROSS WEIGHT 2443.4 LB

REFERENCE WING AREA 138.00 SQ FT

WING LOADING 17.71 LB/SQ FT

THRUST PER ENGINE 419.8 LB

ENGINE SCALE FACTOR 1.0000

THRUST-WEIGHT RATIO 0.1718

Geometry:Span = 38 ft.Wing Area = 138 sq.ft.AR = 10.4Taper Ratio = 0.446Sweep = 7.0°Dihedral = 20°Thickness to chord of wing (weighted ave.) = 0.12

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Conceptual Sizing and SynthesisConceptual Sizing and Synthesis

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Conceptual Sizing and Synthesis - SummaryConceptual Sizing and Synthesis - Summary

Using project 1 sizing and synthesis Fixed Wing Conceptual Design Tool: Mission analysis (summary, table)

Constraint analysis (plot)

Final design point and estimated TOGW

Briefly Summarize sizing exercise and document key assumptions

Design point (from conceptual design tool):

− T/W = 0.14

− W/S = 17.0

− W_0 = 2,348 lbs

− W_E = 1,408 lbs

− W_C+P = 2,209 lbs

− Wing Area = 138 sq.ft.

− Required Thrust = 328.7 lbs.

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Conceptual Sizing and Synthesis – Conceptual Sizing and Synthesis – 3-View3-View

Graphical Model (3-view)

38’

24’

8’ – 4 bladed


8

Conceptual Sizing and Synthesis – Mission AnalysisConceptual Sizing and Synthesis – Mission Analysis

Mission Analysis 800 lbs of payload

Take-Off Gross Weight = 2,348 lbs

Weight Empty = 1,408 lbs

* Note Source

Step 1 Payload Calculations, WPL

400 lbs240 lbs160 lbs

Total WPL 800 lbs

Step 2 Weight Take Off Guess Based on Historical Data, WTO_GUESS

W_E W_TO V_cruise Range(lbs) (lbs) (kts) (nm)

2,050 3,000 150 777 2,225 3,400 185 1,170

Average: 3,200 168 974 WTO_GUESS 2,348 lbs

Step 3 Mission Fuel Weight Fractions, WF

Profile Weight Fractions:W1/WTO 0.995

W2/W1 0.998

W3/W2 0.992

W4/W3 0.961

W5/W4 0.994

Total Fuel Fraction WL/WTO 0.941

Total Weight of Fuel Required WF 139 lbs

Gallons of Fuel 23.2 galMiles per Gallon 30.18 mpg

Step 4 Initial Operation Weight Empty, WOE

WOE 1,408 lbs

Step 5 Initial Weight Empty, WE

WTFO - lbs

WE 1,408 lbs

Step 6 Allowable Weight Empty From Historical Data, WE_HIST

A Regression Const. (Single Engine Prop) -0.144B Regression Const. (Single Engine Prop) 1.1162

Weight Empty from Historical Data WE_HIST 1,408 lbs

Step 7 Adjust Take Off Weight Guess Until WE = WE_HIST

First IterationWE 1,408 lbs

WE_HIST 1,408 lbs

Error (0) lbs

Loiter for 45 min. @ 5,000ft

Warm-up Taxi

Max Performance Take-Off @ SL

Max Power Climb to Opt. Alt.

Cruise out 700 nm @ Optimum Speed/Alt

Aircraft Type

2 Pilots

CIRRUS SR20CIRRUS SR22

2 PassangersBaggage

WOE = WTO_GUESS - WF - WPL

WE = WOE - WTFO - WCREW

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Conceptual Sizing and Synthesis – Mission SummaryConceptual Sizing and Synthesis – Mission Summary

Mission Summary 700 miles range (608.3 nautical miles)

139 lbs of Fuel (23.2 gal)

30 mpg (Design requirement)

* Note Source

Seg. Description Altitude Temp. Density Velocity Range q CL CD L/D Wn-1/Wn Fuel Burn Fuel Weight Beta

(ft) (°F) slug/ft^3 knots nm psf (lbs) (lbs) (lbs)0 0 59.0 2.377E-03 0.0 - 0 0.0000 0.0097 0.00 1.000 - - 2,348 1.0001 Warm-up Taxi 0 59.0 2.377E-03 0.0 - 0 0.0000 0.0097 0.00 0.995 12 12 2,336 0.9952 Max Perforamnce Take-Off @ SL 0 59.0 2.377E-03 67.1 - 15 1.2000 0.1341 8.95 0.998 16 5 2,331 0.9933 Max Power Climb to Opt. Alt. 10,000 23.4 1.755E-03 73.2 14 18 0.9371 0.0611 15.34 0.992 35 19 2,313 0.9854 Cruise out 700 miles @ Optimum Speed/Alt 10,000 23.4 1.755E-03 178.0 608 79 0.2114 0.0113 18.78 0.961 125 90 2,222 0.9475 Loiter for 20 min. @ 5,000ft 5,000 41.2 2.048E-03 110.0 608 35 0.4559 0.0171 26.66 0.994 139 14 2,208 0.941

Mission Summary

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0.0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0 10 20 30 40 50 60 70 80

Conceptual Sizing and Synthesis – Constraint AnalysisConceptual Sizing and Synthesis – Constraint Analysis

Design SpaceDesign Space

Design PointDesign Point

T/W = 0.14T/W = 0.14W/S = 17.0W/S = 17.0

Thr

ust

Load

ing,

T/W

Wing Loading, W/S

Take off 3,000 ft

, 50 ft

obstacle, V_stall <

61 kts

Lan

din

g d

ista

nce

3,0

00 f

t, V

_TD

>=

1.15

V_s

tall

Climb 300 fpm, V_CL >= 1.2V_stall

V_stall < 61 kts

Service Ceiling 15,000 ft

Cruise Speed > 200 mph

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput

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Construct Working FLOPS File

Convey information and assumptions form conceptual phase have carried over to FLOPS: started preliminary sizing with output from conceptual design phase: T/W 0.14 and W/S 17.0

What information (assumed or inferred) from the vehicle concept description Sizing Mission –

− Payload: 2+2 Pax + baggage (400 + 240 + 160 lbs = 800 lbs total)

− Block Fuel Burn: > 30 miles per gallon

− Range: 700 miles (608.3 nm)

− Loiter: 45 minutes, end of mission

Design Constraints –− Cruise Speed: > 200 mph (174 knots)

− TOFL: 3000 ft, over 50 ft obstacle

− V_stall < 61 kts Stall

− V_TO >= 1.1 V_stall Takeoff

− V_CL >= 1.2 V_stall Climb

− V_A >= 1.3 V_stall Approach

− V_TD >= 1.15 V_stall Touchdown

− Climb: 300 fpm @SLS

Source (2)

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Design Point − Started preliminary sizing with T/W = 0.14, W/S = 17.0

− Attempt to match the 329 lbs of thrust requirement

− 30 mpg

− Max Cruise Altitude =12,000 ft.

− 3,000 ft. runway

Geometry parameters (from output of conceptual design) − Wing:

• Span = 38 ft.

• Wing Area = 138 sq.ft.

• AR = 10.4

• Taper Ratio = 0.446

• Sweep = 7.0°

• Dihedral = 20°

• Thickness to chord of wing (weighted ave.) = 0.12

− Fuselage

• Length = 24 ft.

• Width = 3.44 ft.

• Depth = 4.59 ft.

− Vertical = 25.0 sq.ft.

− Horizontal = 23.7 sq.ft.

Source (2)

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Propulsion and power plant parameters:

− TELEDYNE CONTINENTAL MOTORS - IO-360-ES (X – Modified for 2,027 tech.)

− 250 HP (Modified for 2,027 tech.)

− Min SFC 0.35 (modified for 2,027 tech.)

− Six cylinders horizontally opposed

− Four strokes, Fuel injected, Spark ignition, Direct drive

− Air-cooled

− Wet sump engine, Incorporating a top induction system, bottom exhaust.

− Height 22.43 in.

− Width 31.46 in.

− Length 34.03 in.

Source (4)

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Aircraft type – Single engine, tail sitter, low wing

Aircraft class – Family four passenger

Percent of Materials used – Airframe 85% composites

Technology year - 2027

Intermediary and Final Calculations To obtain the required efficiency the RPM was varied to achieve 30 mpg

To obtain the required rate of climb the engine power was increased from 210 hp to 250 hp

To obtain the required take off distance wing CL max was increased to CL = 2.0

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - OutputOutput

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Conceptual Sizing and Synthesis – Conceptual Sizing and Synthesis – 3-View3-View

Graphical Model (3-view) FINAL DESIGN

38’

24’

6.5’ – 6 bladed


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High Efficiency Wing DesignHigh Efficiency Wing Design

High Aspect RatioHigh Aspect Ratio Advanced Feather TipAdvanced Feather Tip

Combination of advance Combination of advance tips and high aspect ratio tips and high aspect ratio balance Aerodynamics balance Aerodynamics with Manufacturabilitywith Manufacturability

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - WeightWeight

Weight Breakdown Table + user defined percentage of usage of composites and non-traditional

materials

Glass cockpit flight instruments VOR/ILS/GPS navigation w/on-board map Limited auto-pilot features (altitude and heading hold)

Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)

Source (3)

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - WeightWeight

Weight Breakdown

Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)

MASS AND BALANCE SUMMARY PERCENT WREF POUNDSWING 12.19 298

HORIZONTAL TAIL 0.00 0VERTICAL TAIL 0.00 0

FUSELAGE 20.09 491LANDING GEAR 3.69 90

NACELLE (AIR INDUCTION) 0.00 0STRUCTURE TOTAL 35.96 879

ENGINES 13.39 327THRUST REVERSERS 0.00 0

MISCELLANEOUS SYSTEMS 0.00 0FUEL SYSTEM-TANKS AND PLUMBING 0.82 20

PROPULSION TOTAL 14.22 347SURFACE CONTROLS 2.81 69

AUXILIARY POWER 0.00 0INSTRUMENTS 0.74 18

HYDRAULICS 0.33 8ELECTRICAL 0.41 10

AVIONICS (Includes: Glass Cockpit, VOR/ILS, Limited Auto Pilot 3.91 96

Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features) 2.86 70

AIR CONDITIONING 0.00 0ANTI-ICING 0.00 0

SYSTEMS AND EQUIPMENT TOTAL 11.07 271

WEIGHT EMPTY 61.25 1,497

CREW AND BAGGAGE-FLIGHT, 0 0.00 0-CABIN, 0 0.00 0

UNUSABLE FUEL 0.25 6ENGINE OIL 0.17 4

PASSENGER SERVICE 0.00 0CARGO CONTAINERS 0.00 0

OPERATING WEIGHT 61.67 1,507

PASSENGERS, 4 32.74 800PASSENGER BAGGAGE 0.00 0

CARGO 0.00 0

ZERO FUEL WEIGHT 94.41 2,307

MISSION FUEL 5.59 137

RAMP (GROSS) WEIGHT 100.00 2,443

Structure 85% Composites:-Wing-Tail-Fuselage

Final WE = 1,497Final WE = 1,497Final TOGW = 2,443Final TOGW = 2,443

Source (3, 4)

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - PropulsionPropulsion

Propulsion and Powerplant Description of powerplant

− 250 HP

− Six cylinders horizontally opposed

− Low RPM (1,600 RPM)

− High Efficiency (0.35 SFC)

Number of Engines = 1

Placement – Front Mounted

Source (4)

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Propulsion and Powerplant Thrust vs. Altitude curves for varying Mach number

-

2,000

4,000

6,000

8,000

10,000

12,000

200 250 300 350 400 450

Thrust (lbs)

Altitude (ft)

Standard Day

0.28 0.24 0.20 0.16 0.12 0.08 0.04 0.00

Mach #:

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Propulsion and Powerplant Fuel consumption curves

-

2,000

4,000

6,000

8,000

10,000

12,000

0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4

SFC (lbsm/lbs hour )

Altitude (ft)

0.00 0.04 0.08 0.12 0.16 0.20 0.24 0.28

Mach #:

Standard Day

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - AerodynamicsAerodynamics

Aerodynamics Basic aerodynamic description of aircraft

• Span = 28 ft.

• Wing Area = 138 sq.ft.

• AR = 10.4

• Taper Ratio = 0.446

• Sweep = 7.0°

• Dihedral = 20°

• Thickness to chord of wing (weighted ave.) = 0.12

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - AerodynamicsAerodynamics

Aerodynamics Drag polar for varying Mach number (graph)

0

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1

CD

CL

Mach = 0.2Mach = 0.3Mach = 0.4Mach = 0.5

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - MissionMission

Mission Performance: Mission profile (schematic)

* * * M I S S I O N S U M M A R Y * * *

INITIALSEGMENT WEIGHT(LB) SEGMT TOTAL SEGMT TOTAL SEGMT TOTAL START END START END

TAXI OUT 2,443.0 1.0 1.0 5.0 5.0TAKE OFF 2,442.0 0.0 1.0 1.2 6.2 0.1 0.0

CLIMB 2,442.0 8.0 10.0 11.8 18.0 21.4 21.4 0.1 0.3 0.0 10,000.0CRUISE 2,434.0 92.0 101.0 192.8 210.7 553.8 575.1 0.3 0.3 10,000.0 10,000.0

DESCENT 2,342.0 2.0 103.0 22.6 233.4 33.2 608.3 0.3 0.1 10,000.0 0.0APPROACH 2,340.0 2.0 105.0 4.0 237.4

RESERVES 2,338.0 32.0 137.0TAXI IN 1.0 3.0 240.4

ZERO FUEL 2,307.0

DESIGN RANGE 608.3 FLIGHT TIME 227.2

BLOCK TIME = 4.01 HOURS BLOCK FUEL = 105.6 POUNDS

ATA TRAFFIC ALLOWANCE = 46.8 NAUTICAL MILES AIR MANEUVER = 17.2 AIRPORT TRAFFIC ALLOWANCE = 17.4 AIRWAY DISTANCE FACTOR = 12.2

ATA RANGE = 608.3 NAUTICAL MILES

ALTITUDE (FT)FUEL (LB) TIME (MIN) DISTANCE (N MI) MACH NUMBER

17.6 Gallons

700 miles (608.3 nm)39.7 mpg39.7 mpg

TO @ SL, Standard

10,000 ft Altitude Cruise @ 200mph 45 min Loiter

Land @ SL, Standard

700 Miles

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Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - MissionMission

Mission Performance: Instantaneous cruise data:

WEIGHT ALTITUDE MACH NO. THRUST FUEL FLOW EX POW CLIFT LIFT L/D ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC CDRAG(lbs) (ft) (lbs) (lb/hr) HP (lbs) (kts) (min) (nm) (lb)

2434 10000 0.27 198 29 372.4 0.23743 2434 12.314 11315 172.35 17.97 21.4 10 0.79193 0.14466 0.019282394 10000 0.27 198 29 379.1 0.23355 2394 12.117 11315 172.35 101.39 261 49 0.79165 0.14469 0.019272388 10000 0.27 198 29 380.1 0.23296 2388 12.087 11315 172.35 113.99 297.2 55 0.79162 0.1447 0.019272382 10000 0.27 198 29 381.1 0.23238 2382 12.058 11315 172.35 126.58 333.4 61 0.79159 0.1447 0.019272376 10000 0.27 198 29 382.1 0.23179 2376 12.028 11315 172.35 139.17 369.5 67 0.79156 0.1447 0.019272370 10000 0.27 198 29 383.2 0.23121 2370 11.998 11315 172.35 151.77 405.7 73 0.79153 0.14471 0.019272364 10000 0.27 198 29 384.2 0.23062 2364 11.968 11315 172.35 164.36 441.9 79 0.7915 0.14471 0.019272358 10000 0.27 198 29 385.2 0.23004 2358 11.938 11315 172.35 176.96 478.1 85 0.79147 0.14471 0.019272352 10000 0.27 198 29 386.2 0.22945 2352 11.908 11315 172.35 189.55 514.2 91 0.79145 0.14472 0.019272346 10000 0.27 198 29 387.3 0.22887 2346 11.878 11315 172.35 202.15 550.4 97 0.79143 0.14472 0.019272342 10000 0.27 198 29 388 0.22847 2342 11.857 11315 172.35 210.74 575.1 101 0.79141 0.14472 0.01927

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Preliminary Sizing and Synthesis – Preliminary Sizing and Synthesis – Constraint AnalysisConstraint Analysis

Constraint Analysis: After completing the FLOPS

preliminary design analysis, the required thrust went from 329 lbs to 419 lbs

Keeping the wing area the same the wing loading went up to W/S = 17 to 17.74 psf

Conceptual Design Point

Preliminary Design Point

T/W = 0.14

TOGW = 2,348 lbs

WE = 1,408 lbs

Thrust = 329 lbs

T/W = 0.178

TOGW = 2,443 lbs

WE = 1,507 lbs

Thrust = 419

W/S = 17

S = 138 sq.ft.

W/S = 17.71

S = 138 sq.ft.

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Preliminary Sizing and Synthesis – Preliminary Sizing and Synthesis – Constraint AnalysisConstraint Analysis

Landing Requirements: Take off, DFAROFF = 2,227 ft < 3,000 ft

Landing, DFARLDG = 2,817 ft < 3,000 ft.

Stall Requirements: STALL SPEED (VS) = 51.14 kts < 61 kts

1.05 VS 53.69 kts

1.20 VS 61.36 kts

Miles per Gallon = 39.7 > 30.0

Cost/AC = $58 Million > $150,000 Maybe I made a mistake?

ExceededExceededExceededExceeded

ExceededExceeded

ExceededExceeded

Not MetNot Met

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ConclusionsConclusions

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ConclusionsConclusions

Using the FLOPS program an aircraft with the range of 700 miles @ 200 mph was designed: The table below summarizes the key parameters for the Mensa XE

Further detail into engine design would be the next step, specifically: Efficiency

Fuel type

Engine size

FINAL FLOPS SIZING AND PERFORMANCE RESULTS

OPERATING WEIGHT EMPTY 1506.7 LB

PAYLOAD 800.0 LB

MAXIMUM FUEL 136.6 LB

GROSS WEIGHT 2443.4 LB

REFERENCE WING AREA 138.00 SQ FT

WING LOADING 17.71 LB/SQ FT

THRUST PER ENGINE 419.8 LB

ENGINE SCALE FACTOR 1.0000

THRUST-WEIGHT RATIO 0.1718

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References:References:

(1) AE 6343 Aircraft Design Project #2, -2007, “Sizing and Synthesis with a Legacy Tool for Distance Learning Students”, Hernando Jimenez

(2) Flight Optimization System, Release 6.12, User's Guide, Revised 14, October 2004, L.A. (Arnie) McCullers

(3) http://www.cirrusdesign.com/sr20/features.aspx

(4) http://www.tcmlink.com/EngSpecSheetDocs/IO360G.pdf

Documents

Mensa XE (Extra Efficiency) High Efficiency Family Airplane