Tunnel tests to obtain characteristics of control surfaces; symmetrical double wedge airfoil of 7% thickness, with 15 and 30% trailing edge flaps, used as model; pressure measurements and Schlieren photographs taken in two-dimensional channel at Mach numbers 1.38, 1.48 and 1.58.
Supersonic tests of conventional control surfaces on double-wedge airfoil
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 17 , n 4
1950
7 pages
Aufsatz (Zeitschrift)
Englisch
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