Accession Number : AD0640278

Title :   HYPERSONIC FLOW OVER LIFTING WING-BODY COMBINATIONS,

Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CALIF

Personal Author(s) : Malmuth,N. D.

Report Date : 01 JUN 1966

Pagination or Media Count : 17

Abstract : Using linear rotational flow methods within the framework of Hypersonic Small Disturbance Theory, the flow over a class of lifting wing-body combinations is analyzed. These configurations consist of a delta wing mounted on top of a slender ruled body of arbitrary cross section, contained within the parabolic Mach cone. Solutions for the shock shape, lift and the pressure field between the body and shock are obtained using eigenfunction techniques developed in connection with other wedge-like flows. Recommendations are made for future extensions of the analysis involving the determination of optimum contouring as well as treatment of more general classes of bodies. (Author)

Descriptors :   (*WING BODY CONFIGURATIONS, *HYPERSONIC FLOW), AERODYNAMICS, BOUNDARY VALUE PROBLEMS, LIFT, DELTA WINGS, PRESSURE, CONICAL BODIES, FUNCTIONS(MATHEMATICS), SHOCK WAVES

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE