Free stream noise and transition measurements in a Mach 3.5 pilot quiet tunnel-Reference-Cited by-同舟云学术

Free stream noise and transition measurements in a Mach 3.5 pilot quiet tunnel

Published:1983-01-10 Issue: Volume: Page:
ISSN:
Container-title:21st Aerospace Sciences Meeting
language:
Short-container-title:

Author:

BECKWITH I.¹,CREEL, JR. T.¹,CHEN F.-J.¹,KENDALL J.²

Affiliation:

1. NASA, Langley Research Center, Hampton, VA

2. NASA, Langley Research Center,Hampton, VA; California Institute of Technology, Jet Propulsion Laboratory, Pasadena, CA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1983-42

Reference42 articles.

1. Radiated aerodynamic noise effects on boundary-layer transition in supersonic and hypersonic wind tunnels.

2. A cascade connected electrode scheme for MHD applications.

3. 4Uougnerty, N. S., Jr. and Fisher, 0. F.: Boundary-Layer Transition on a 10 Oeg Cone: Wind TunnelIFliqnt Correlation. AIAA Paper 80-0134, January lY&

4. Development of a High Reynolds Number Quiet Tunnel for Transition Research

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