Shock expansion method described in Tech Note n 1143, separately indexed, was used to determine principal aerodynamic characteristics of supersonic airfoils; effect of thickness ratio, free stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection; minimum drag of supersonic airfoils obtained when maximum thickness is behind 0.50 chord.
Notes on theoretical characteristics of two-dimensional supersonic airfoils
Nat Advisory Committee Aeronautics -- Tech Note
1947
9 pages
14 Supp Plates
Report
Englisch
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