Detection of turbulent boundary-layer separation using fluctuating wall pressure signals
Author:
Affiliation:
1. The University of Texas at Austin, Austin, Texas
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.25164
Reference13 articles.
1. Settles, G. S. "An Experimental Study of Compressible Turbulent Boundary Layer Separation at High Reynolds Numbers," Ph.D. Dissertation, Mechanical and Aerospace Engineering Dept.Princeton Univ., Sept. 1975.
2. Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
3. Unsteadiness of the shock wave structure in attached and separated compression ramp flows
4. Structure of the wall pressure fluctuations in a shock-induced separated turbulent flow
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