Control of Supersonic Inlet-Isolator Unstart Using Active and Passive Vortex Generators

Author:

Valdivia A.1,Yuceil K. B.2,Wagner J. L.1,Clemens N. T.1,Dolling D. S.1

Affiliation:

1. Center for Aeromechanics Research, The University of Texas at Austin, Austin, Texas 78712-1085

2. Department of Astronautical Engineering, Istanbul Technical University, 34469 Istanbul, Turkey

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Reference49 articles.

1. CurranE. T.StullF. D. “The Utilization of Supersonic Combustion Ramjet Systems at Low Mach Numbers,” Aero Propulsion Lab. Rept. RTD-TDR-63-4097, Wright-Patterson AFB, OH, Jan. 1964.

2. Fluid Phenomena in Scramjet Combustion Systems

3. EmamiS.TrexlerC. A.AuslenderA. H.WeidnerJ. P. “Experimental Investigation of Inlet-Combustor Isolators for a Dual Mode Scramjet at a Mach Number of 4,” NASA TP-3502, May 1995.

4. Analysis of Flows in Scramjet Isolator Combined with Hypersonic Inlet

5. Effects of Hypersonic Inlet Flow Non-Uniformities on Stabilising Isolator Shock Systems

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