Forebody Compressibility Research of Hypersonic Vehicle

LIU Jia; YAO Wen-xiu; LEI Mai-fang; WANG Fa-min

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Article Navigation > Applied Mathematics and Mechanics > 2004 > 25(1): 85-92

LIU Jia, YAO Wen-xiu, LEI Mai-fang, WANG Fa-min. Forebody Compressibility Research of Hypersonic Vehicle[J]. Applied Mathematics and Mechanics, 2004, 25(1): 85-92.

Citation:

LIU Jia, YAO Wen-xiu, LEI Mai-fang, WANG Fa-min. Forebody Compressibility Research of Hypersonic Vehicle[J]. Applied Mathematics and Mechanics, 2004, 25(1): 85-92.

Citation:

LIU Jia, YAO Wen-xiu, LEI Mai-fang, WANG Fa-min. Forebody Compressibility Research of Hypersonic Vehicle[J]. Applied Mathematics and Mechanics, 2004, 25(1): 85-92.

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Forebody Compressibility Research of Hypersonic Vehicle

Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080, P. R. China

Received Date: 2002-05-30
Rev Recd Date: 2003-07-31
Publish Date: 2004-01-15

Abstract

Abstract

Three kinds of forebody model of hypersonic vehicles were studied with numerical simulation method.It shows that the two-order compressive ramp model is the best selection among the three for its good evaluative parameters value at the cowl of the inlet.This model can provide higher value of flux coefficient and total pressure recovery coefficient and lower average Mach number compared with those of the other two models.Simultaneously different compressive angles may have different effects.The configuration which the first order of compressive angle is 4° and the second 5° is the optimum combination.Furthermore factors such as attack angle were concerned.Better result may be obtained with a range of attack angles.Based on the work above the integrated design for forebody/inlet of a hypersonic vehicle was performed.The numerical result shows that this integrated model provides good flow field quality for inlet and engine work.
- hypersonic vehicle,
- integration of forebocphy-inlet,
- compressibility

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References(8)

References

[1]	Hiroaki Kobyashi, Tetsuya Sato, Nobuhiro Tanataugu.Optimization of airbreathing propulsion system for the TSTO spaceplane[R]. AIAA,2001-1912.
[2]	Tsuchiya T, Mori T,Maita M. An integrated optimization for conceptual designs of airbreathing launch TSTO vehicle[R]. AIAA,2001-1902.
[3]	Ryan P,Starkey Mark,Lewis J. Critical design issues for airbreathing hypersonic waverider missiles[J].Journal of Spacecraft and Rockets,2001,38(4):510—519. doi: 10.2514/2.3734
[4]	von Eggers Lael, Rudd Darryll, Pines J. Integrated propulsion effects on dynamic stability and control of hypersonic waveriders[R]. AIAA,2000-3826.
[5]	James L Hunt. NASA's dual-fuel airbreathing hypersonic vehicle study[R]. AIAA,1996-4591.
[6]	O′Neil M K L ,Lewis M J. Design tradeoffs on scramjet engine integrated hypersonic waverider vehicles[J].Journal of Aircraft, 1993,30(6): 943—952. doi: 10.2514/3.46438
[7]	O′Neil M K L， Lewis M J. Optimized scramjet integration on a waverider[J].Journal of Aircraft,1992,29(6):1114—1121. doi: 10.2514/3.56866
[8]	Thomas J.Boagar. Dual-fuel lifting body configuration development[R]. AIAA,1996-4592.