Unsteady Separation in Flare-Induced Hypersonic Shock-Wave Boundary-Layer Interaction Flowfield
Author:
Affiliation:
1. Hyperschall Technologie Gottingen, 37191 Katlenburg-Lindau,Germany
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/2.3831
Reference10 articles.
1. Fluctuating Wall Pressure under a Separated Supersonic Flow
2. Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
3. Hypersonic flow over axially symmetric spiked bodies
4. An experimental investigation of the unsteady behavior of blunt fin-induced shock wave turbulent boundary layer interaction
5. New Diagnostic Technique for the Study of Turbulent Boundary-Layer Separation
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2. Spatial and temporal alterations due to vortex generators in a flare induced shock–boundary layer interaction;European Journal of Mechanics - B/Fluids;2023-05
3. Performance evaluation of different micro vortex generators in controlling a flare-induced shock–boundary layer interaction;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2022-11-16
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