Accession Number:

ADA801407

Title:

Notes on the Theoretical Characteristics of Two-Dimensional Supersonic Airfoils

Personal Author(s):

Corporate Author:

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY

Report Date:

1947-01-01

Abstract:

The shock-expansion method of 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.

Descriptive Note:

Technical note

Pages:

0027

Communities Of Interest:

Distribution Statement:

Approved for public release; distribution is unlimited. Document partially illegible.

File Size:

2.09MB