Control of Incident Shock-Induced Separation Using Vane-Type Vortex-Generating Devices
Author:
Affiliation:
1. National Aerospace Laboratories, Bangalore 560 017, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J056460
Reference61 articles.
1. Fifty Years of Shock-Wave/Boundary-Layer Interaction Research: What Next?
2. Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
3. Unsteadiness in shock wave boundary layer interactions with separation
4. Reduction of fluctuating pressure loads in shock/boundary-layer interactions using vortex generators
5. Some physical aspects of shock wave/boundary layer interactions
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