Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation-Reference-Cited by-同舟云学术

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Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation

Published:1991-08-17 Issue: Volume: Page:
ISSN:
Container-title:3rd International Aerospace Planes Conference
language:
Short-container-title:

Author:

MCDANIEL JAMES¹,FLETCHER DOUGLAS²,HARTFIELD ROY¹,HOLLO STEVEN¹

Affiliation:

1. Virginia, University, Charlottesville

2. NASA, Ames Research Center, Moffett Field, CA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1991-5071

Cited by 23 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. Numerical investigation of annular expansion-deflection nozzle flow under varying backpressure changing rate;Chinese Journal of Aeronautics;2024-08

2. Numerical Investigation of Confinement Effect on Supersonic Turbulent Flow Past Backward Facing Step With And Without Transverse Injection;Journal of Aerospace Sciences and Technologies;2023-08-07

3. Spectral Content in a Supersonic Backward-Facing Step Flow;Journal of Spacecraft and Rockets;2021-01

4. Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave;International Journal of Turbo & Jet-Engines;2019-03-22

5. Structures and aero-optical effects of supersonic flow over a backward facing step with vortex generators;European Journal of Mechanics - B/Fluids;2019-03

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