Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.
The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.
- Arthur Kantrowitz, Eric Reissner, Frank S. Malvestuto, George R. Costello, Harold I. Johnson, Melvin E. Laverne, Warren A. Tucker, United States. National Advisory Committee for Aeronautics, Kenneth Margolis, Leo Diesendruck, Melivn E. Laverne, Richard Hood, Robert L. Nelson, Aaron S. Boksenbom, Bertham J. Eisenstadt
· 1950
- Kenneth Margolis
· 1948
Wave drag equations are derived for rhombic-profile tapered wings with maximum-thickness line swept less than the Mach line. Variations in drag with taper ratio, aspect ratio, sweepback, and Mach number are determined. Calculations are presented for representative plan forms and for a family of wings having equal root bending stress.
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