Design and wind tunnel testing of intakes for hypersonic vehicles-Reference-Cited by-同舟云学术

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Design and wind tunnel testing of intakes for hypersonic vehicles

Published:1993-08-22 Issue: Volume: Page:
ISSN:
Container-title:5th International Aerospace Planes and Hypersonics Technologies Conference
language:
Short-container-title:

Author:

Bissinger N.¹,Schmitz D.¹

Affiliation:

1. Deutsche Aerospace AG, Munich, Germany

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1993-5042

Reference9 articles.

1. W.F.Wong The Applicationof BoundaryLayer SuctiontoSuppress StrongShock-InducedSeparation in SupersonicInlets AIAA/ SAE 10thPropulsionConference,SanDiego. PaperNo. 74-1063.Oct. 1974

2. A.Eberle,M.A. Schmatz,N.C.Bissinger GeneralizedFluxVectorsforHypersonicShock-Capturing AIAA-90-0390

3. E.H.Hirschel DasCousteix-Verfahren zurBerechnungturbulenter dreidimensionalerGrenzschichteninderMBBFassung MBB/UFE/RO/MT/469,1980, unpublished

Cited by 2 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Aerothermodynamic Design Problems of Winged Airbreathing Vehicles;Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles;2009

2. Design and testing of 2-D fixed-geometry hypersonic intakes;8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference;1998-04-27

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