Accession Number : AD0623167

Title :   SUPERSONIC LIFT SOLUTIONS OBTAINED BY EXTENDING THE SIMPLE LINEARIZED CONICAL FLOW THEORY,

Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CALIF

Personal Author(s) : Coleman,T. F.

Report Date : 31 OCT 1947

Pagination or Media Count : 28

Abstract : Results of the linearized conical supersonic flow theory for flat plate wings are extended to the treatment of certain planforms which cannot be solved by the simple methods of superposition previously described. The method described in the report is applicable to wings with subsonic trailing edges (within certain limitations) and to regions in which the flow is affected by more than one disturbance. Solutions are obtained by superposing conical flow fields resulting from elementary wings with certain special properties, to the basic wings required; this superposition is accomplished by integrating the contribution of an infinite number of such elementary wings, plus the contributions from the basic wings obtained in the usual manner. The elementary wings used are chosen in such a way that the boundary conditions of the wing to be solved are satisfied by the integrated solution. The method is applied to obtain expressions for the pressure distributions on a low aspect ratio rectangular wing, a triangular wing with cut-off wing tips, and a diamond wing. (Author)

Descriptors :   (*WINGS, AERODYNAMIC CHARACTERISTICS), (*TRAILING CONTROL SURFACES, LIFT), (*LIFT, MATHEMATICAL ANALYSIS), SUPERSONIC FLOW, SUBSONIC FLOW, FLAT PLATE MODELS, DELTA WINGS, THEORY, LINEAR SYSTEMS, RECTANGULAR BODIES, CONICAL BODIES

Distribution Statement : APPROVED FOR PUBLIC RELEASE