Acoustic technique for detection of flow transition on hypersonic re-entry vehicles
Author:
Affiliation:
1. Bolt Beranek and Newman lnc., Cambridge, Mass.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.5520
Reference7 articles.
1. Dynamics of an Acoustic Probe for Measuring Pressure Fluctuations on a Hypersonic Re‐Entry Vehicle
2. Hypersonic laminar boundary-layer transition on 8-foot-long, 10 deg cone, M sub 1 equals 9.1-16.
3. Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flows
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