Characterization of Bleedless Shockwave Boundary Layer Interaction Control for High Speed Intakes
Author:
Affiliation:
1. Florida State University
2. Defence Science and Technology Laboratory
3. Air Force Research Laboratory
Publisher
American Institute of Aeronautics and Astronautics
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1. Two-dimensional generic inlet unstart detection at Mach 2.5-5.0
2. Effect of back pressure and freestream dynamic pressure on a typical Ramjet engine duct under realistic supersonic inlet condition
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1. Effect of Incoming Boundary Layer Thickness on the Flow Characteristics of a Supersonic Air Intake;AIAA AVIATION 2023 Forum;2023-06-08
2. Flow instabilities and impact of ramp–isolator junction on shock–boundary-layer interactions in a supersonic intake;Journal of Fluid Mechanics;2022-12-09
3. Linear and Nonlinear Flow Analysis of Elements of a Supersonic Inlet;AIAA Journal;2021-11
4. Direct Numerical Simulation of the Pulsed Arc Discharge in Supersonic Compression Ramp Flow;Journal of Thermal Science;2020-09-26
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