Accession Number : AD0634146

Title :   LINEAR, ROTATIONAL FLOW OVER THE WINDWARD SIDE OF A HYPERSONIC DELTA WING.

Descriptive Note : Interim rept.,

Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CALIF

Personal Author(s) : MALMUTH, Norman D.

Report Date : 1966

Pagination or Media Count : 38

Abstract : The hypersonic flow over the compression side of a delta wing is analyzed within the framework of Van Dyke's Small Disturbance Theory and the assumption that the vertex angle of the Mach cone bounding the central nonuniform interaction region is small in comparison to the wing apex angle. Asymptotic expansions of the flow quantities in terms of a small parameter equal to the ratio of the tangents of these angles are introduced. The leading terms in these expansions correspond to the flow over a wedge of semivertex angle equal to the incidence of the delta wing, and the second order terms are linear rotational perturbations due to the three-dimensional interaction across the wing. By use of methods previously developed for other wedge-like hypersonic conefields, the lift, shock shape and pressure field over the wing are obtained. Perturbation and total quantites are compared with results from the numerical solution of Babaev giving good qualitative agreement for the former and satisfactory quantitative accord for the latter, within the assumptions of the theory. (Author)

Descriptors :   (*DELTA WINGS, *HYPERSONIC FLOW), (*AERODYNAMICS, DELTA WINGS), VORTICES, PERTURBATION THEORY, FLUID FLOW, NUMERICAL ANALYSIS

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE