Studies of transition over flat plate at Mach Number 1.76 carried out using hot wire anemometer as one of principal tools; nature and measurements of free stream disturbance at supersonic speeds, analyzed; results interpreted in light of present overall information on transition at supersonic speeds; conclusions as to further experiments.
On transition experiments at moderate supersonic speeds
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 24 , n 7
1957
7 pages
Article (Journal)
English
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Maximum lift-to-drag ratio airfoils at moderate supersonic speeds
Engineering Index Backfile | 1969
|Factors affecting transition at supersonic speeds
NTRS | 1953
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