Investigation of the Flow Field of a 2D SCRAM Jet Inlet at Mach 7 with optional Boundary Layer Bleed-Reference-Cited by-同舟云学术

Investigation of the Flow Field of a 2D SCRAM Jet Inlet at Mach 7 with optional Boundary Layer Bleed

Published:2007-07-08 Issue: Volume: Page:
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Container-title:43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
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Author:

Häberle Jürgen,Gülhan Ali

Publisher

American Institute of Aeronautics and Astronautics

Reference13 articles.

1. Voland, R. T., et. al. "Hyper-X Engine Design and Ground Test Program", AIAA-98-1532,AIAA 8thInternational Space Planes and Hypersonic Systems and Technologies Conference, NASA Langley Research Center,HamptonVA,1998.

2. Häberle, J. Gülhan, A. "Investigation of the Performance of a Scramjet Inlet at Mach 6 with Boundary Layer Bleed", AIAA 2006-8139, 14thAIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, Canberra,2006.

3. Aerodynamic Performance Analysis of a Hypersonic Inlet Isolator Using Computation and Experiment

4. Study on shock wave and turbulent boundary layer interactions in a square duct at Mach 2 and 4

5. Streamline Tracing: Technique for Designing Hypersonic Vehicles

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