Design study results of a supersonic cruise fighter wing

Author:

MILLER D.1,SCHEMENSKY R.2

Affiliation:

1. NASA, Langley Research Center, High Speed Aerodynamics Div., Hampton, Va.

2. General Dynamics Corp., Fort Worth, Tex.

Publisher

American Institute of Aeronautics and Astronautics

Reference19 articles.

1. Sorrells, Russell B.; and Miller, David S. "Numerical Method for Design o f Minimum-Drag Supersonic Wing Camber with Constraints on Pitching Moment and Surface Deformation.'I NASA TN D-7097, 1972.

2. Dollyhigh, Samuel M.; Morris, Odell A.; and Adams, Mary S."Experimental Effects o f Fuselage Camber on Longitudinal Aerodynamic Characteristics o f a Series of Wing-Fuselage Configurations at a Mach Number of 1.41 .'I NASA TM X-3411,1976.

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