Three Dimensional Analysis of a Fully Coupled Hypersonic Air-breathing Inlet-Combustor Flowpath
Author:
Affiliation:
1. U.S. Air Force Research Laboratory
2. Software and Engineering Associates, Inc.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2010-412
Reference15 articles.
1. 1Malo-Molina,F.,Gaitonde,D.,andKutschenreuter,P.“NumericalInvestigationofanInnovativeInwardTurning Inlet,”AIAAPaper2005-4871,June2005.
2. 2Gaitonde, D. and Shang, J. “On 3-D Shock-Wave/Turbulent Boundary Layer Interactions at Mach 4,” AIAA Paper 96-0043,January1996.
3. 4Malo-Molina, F., Gaitonde, D., Ebrahimi, H., and Ruffin, S. “Scramjet Combustor Analysis Integrated to an Innovative InwardTurningInlet,”AIAAPaper2008-4577, 2008.
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