D-SEND

* * *

Wind-tunnel tests for developing

the low-boom design concept demonstrator(D-SEND) Yoshikazu MAKINO, Masayoshi NOGUCHI and Dongyoun KWAK

D-SEND Drop test for Simplified Evaluation of Non-symmetrically Distributed sonic boom

D-SEND#1 2011 5

1)

D-SEND#1 3D-SEND#2

S3CM Silent Super Sonic Concept Model

S3CM

D-SEND#2

D-SEND#2 Fig.1(a) 3S3CM Fig.1(b)

ABBA: Airborne Blimp Boom AcquisitionBMS: Boom Measurement System

S3CM 8m1ton JAXA

2)

D-SEND#2S3CM

S3CM(S-cube Concept Model)W=1000kgLxDia.xSpan=7.7mx0.48mx3.5mSpan=3.5mCL=0.12 M=1.3 H=8km)Swing=4.92m2EGI(INS+GPS)Swing=4.92m2EGI(INS+GPS)

(a) Flight test model (S3CM).

(b) Flight test image. Fig.1 Flight test of D-SEND#2.

S3CM

D-SEND#2CFD

CFDTAS-Code: Tohoku Univ. Aerodynamic Simulation

Code3) NS

Tranair++4) 37.68m

10% *

( 181-0015 6-13-1, E- mail : makino.yoshikazu@jaxa.jp)

This document is provided by JAXA.

6 0 , 10 ,20 , 30 4 0 ,10 ,20 ,30

S3TD: Silent Super Sonic Technology Demonstrator

5)

JAXA 2m 2mP0=80kPa M=1.3, CL=0.12

Fig.2 S3CMS3TD

HPM38: 0.2% 850N/mm2200GPa

0.7mm 0.2

Tranair

Nastran

(a) Aerodynamic analysis and structure analysis models.

0.7mm

(b) Aeroelastic analysis result. Fig.2 Jig shape design of aerodynamic wind-tunnel model.

JAXAWINTEC 2m 2m

40m/s 2.5million28mm

1/338mm

38

Fig.338 77mm

300mm

Cm Cn67mm 215mm

80mm

2° =-10° 20° 15

=0°

Fig.3 JAXA 2mx2m low speed wind-tunnel.

JAXA WINTEC 2m×2m4

P0=80kPa M=0.2~1.43.2~10.5million

Fig.4 2°=-10° 20° 10

WINTEC

28

1Run

WINTEC

This document is provided by JAXA.

JAXA

DAHWIN

Fig.5CFD

Fig.4 JAXA 2mx2m transonic wind-tunnel.

Fig.5 JAXA hybrid wind-tunnel(DAHWIN).

JAXA WINTEC 1m×1mM=1.4, 1.6

23, 25millionFig.6

2°20

3015~20

40

28

WINTEC

Fig.6 JAXA 1mx1m supersonic wind-tunnel.

S3CM2

D-SEND#2

6) Euler CFD

27.68m 5%

28

Fig.7(a)~(c) 33

Fig.7(d)

(a) Upper and aft sting. (b) Upper sting.

(c) Aft sting. (d) Without sting.Fig.7 S3CM low-boom design validation model.

JAXA WINTEC 1m 1mM=1.7

25.5million Fig.8

This document is provided by JAXA.

20mm650mm 0,12,22,32,52mm

1114mm 440mm Fig.9

0mm 3H/L=1.25

=4.2°

3

CFD

Fig.8 Supersonic wind-tunnle test.

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

-0.5 0 0.5 1 1.5

Cp

(X- H)/L

Fig.9 Measured near-field pressure signatures.

(M=1.7, H/L=1.25, =4.26°)

JAXA WINTEC 2m 2m3

P0=80kPa M=1.3 S3CMM=1.4

10.5million Fig.10

28

50mm 1600mm12,22,32,42mm

301 4mm1200mm Fig.11 M=1.4,

H/L=2.0 =4.3°

DAHWIN

CFDDAHWIN

3Hexagrid/FaSTAR7)

CFDCFD

CFD Fig.12Fig.13 Fig.13(b)

Fig.10 Transonic wind-tunnle test.

This document is provided by JAXA.

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

-0.5 0 0.5 1 1.5

Cp

(X- H)/L

Fig.11 Measured near-field pressure signatures.

(M=1.4, H/L=2.0, =4.3°)

(a) Upper and aft sting.

(b) Upper sting.

(c) Aft sting.

(d) Without sting. Fig.12 Model support system correction validation.

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

-0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

Cp

(X- H)/L

H/L=1.0 Support-aSupport-bSupport-dModel-e

-0.04

-0.03

-0.02

-0.01

0

0.01

0.02

0.03

0.04

-0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

Cp

(X- H)/L

H/L=1.0 Corrected_d-(a-b)Model-e

Fig.13 Hexagrid/FaSTAR analysis.

ADS

D-SEND#2

ADS Air Data Sensor

Fig.14Fig.15

ADS

Fig.15Fig.14

ADS

CFD

ADS

ADS

This document is provided by JAXA.

Fig.14 JAXA 2mx2m transonic wind-tunnel test for ADS map (M=0.2~1.2).

Fig.15 JAXA 1mx1m supersonic wind-tunnel test for ADS map (M=1.4~1.7).

D-SEND#2S3CM

3CFD

ADS

ADS

JAXA 2013 8 16D-SEND#2 1

12km 8kmBMS

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”

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This document is provided by JAXA.