Investigation conducted in Langley rectangular high speed tunnel on five supersonic airfoils and, for comparison, on two subsonic airfoils; two-dimensional data obtained by pressure measurements and Schlieren photographs at angles of attack from 0° to 4° for Mach numbers between 0.30 and 0.90 for these 6% thick symmetrical airfoils.
Flow and force characteristics of supersonic airfoils at high subsonic speeds
Nat Advisory Committee Aeronautics -- Tech Note
1947
15 pages
41 Supp Plates, Bibliography
Report
English
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