Accession Number : AD0618294

Title :   ON THE HYPERSONIC FLOW OVER A DELTA WING WITH VERY SUPERSONIC LEADING EDGES.

Descriptive Note : Interim rept. for 1 Jan-7 Mar 65 (Revised ed.),

Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CA

Personal Author(s) : Malmuth, Norman D.

Report Date : 01 JUN 1965

Pagination or Media Count : 10

Abstract : For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.

Descriptors :   *DELTA WINGS, *SUPERSONIC AIRFOILS, HYPERSONIC FLOW, BOUNDARY VALUE PROBLEMS, SHOCK WAVES, PERTURBATION THEORY, NUMERICAL ANALYSIS, FLAT PLATE MODELS, DIFFERENTIAL EQUATIONS.

Distribution Statement : APPROVED FOR PUBLIC RELEASE