Hypersonic Inlet Flow Analysis at Mach 5, 6 and 7-Reference-Cited by-同舟云学术

Hypersonic Inlet Flow Analysis at Mach 5, 6 and 7

Published:2006-01-09 Issue: Volume: Page:
ISSN:
Container-title:44th AIAA Aerospace Sciences Meeting and Exhibit
language:
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Author:

Boon Simon¹,Hillier Richard¹

Affiliation:

1. Imperial College London

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2006-12

Reference8 articles.

1. Figure 14. Deceleration of freestream boundary flow conditions from Mach 7 to Mach 6: density contours at various times, leading to inlet unstart Aerothermodynamic Integration Model," TM X 3365, NASA, 1976.

2. 3E. H. Andrews, E. A. Mackley, W Russell, A. L. Simmonds, "An inlet analysis of for the NASA Hypersonic Research Engine Aerothermodynamic Integration Model," TM X 3038, NASA, 1974.

3. 4E.H.Andrews,etal,"HypersonicResearchEngine/Aerothermodynamic Integration Model,`Experimentalresults.Volume 1: Mach 6 Component Integration and Performance'," TM X 72821, NASA, 1976.

4. 5E.H.Andrews,etal,"HypersonicResearchEngine/Aerothermodynamic Integration Model,`Experimentalresults.Volume 4: Mach 5 Component Integration and Performance'," TM X 72824, NASA, 1976.

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