The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic characteristics of two-dimensional supersonic airfoils. A discussion is given of the effect of thickness ratio, free-stream Mach number, angle of attack, camber, thickness distribution, and aileron deflection. The calculations indicated that the minimum drag of supersonic airfoils is obtained when the maximum thickness is behind the 0.50 chord. The center of pressure obtained for a symmetrical supersonic airfoil was found to be ahead of the 0.50 chord.
Notes on the theoretical characteristics of two-dimensional supersonic airfoils
1947-01-01
Miscellaneous
No indication
English
Notes on theoretical characteristics of two-dimensional supersonic airfoils
Engineering Index Backfile | 1947
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