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Wind tunnel experiments relating to supersonic and hypersonic boundary layer transitionHot-wire anemometry is used to study the origin and growth of 'natural' fluctuations in zero pressure gradient boundary layers and the location of transition to turbulence for several Mach numbers between 1.6 and 8.5. The importance to transition of certain physical mechanisms is examined through comparison of the fluctuation growth with the sound-forcing and stability theories of Mack. The mechanisms are shown to assume varying importance in low supersonic, high supersonic and hypersonic regimes. The effect on transition of cone angle of attack, tip heating, and model vibration is mentioned.
Document ID
19740036130
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kendall, J. M. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena Calif., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 74-133
Report Number: AIAA PAPER 74-133
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 30, 1974
End Date: February 1, 1974
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
74A18880
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

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