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Notes on the theoretical characteristics of two-dimensional supersonic airfoilsThe 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.
Document ID
19930081950
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Ivey, H Reese
Date Acquired
August 16, 2013
Publication Date
January 1, 1947
Report/Patent Number
NACA-TN-1179
Report Number: NACA-TN-1179
Accession Number
93R11240
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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