Accession Number : AD0270609

Title :   HYPERSONIC APPROXIMATION FOR THE INVISCID FLOW OVER CONICAL BODIES WITHOUT AXIAL SYMMETRY AND COMPARISON WITH TESTS AT MACH 8

Corporate Author : POLYTECHNIC INST OF BROOKLYN N Y

Personal Author(s) : ORTLOFF,CHARLES R.

Report Date : JAN 1961

Pagination or Media Count : 1

Abstract : A successive approximation method, based on assumptions valid for hypersonic free stream Mach numbers, is developed for analysis of the inviscid perfect gas flow in the shock layer of non-axisymmetric conical bodies at angles of attack and/or yaw. First and second order analyses for determining shock geometry, and the resulting body pressure distribution, are based upon satisfying the flow tangency condition at the body surface by series expansions about first and second approximation shock waves, respectively; small differences added by superimposed second order corrections indicate rapid convergence of the method, so that first approximation shock geometry and pressure distribution results are sufficient to represent the flow field. First order hypersonic approximation results for an elliptic cone (a/b=1.78), over a large range of angles of attack and yaw, at M1=8.00, indicate accuracy comparable to more complex theoretical methods, and in good agreement with experimental data for lower values of these angles. (Author)

Descriptors :   *CONICAL BODIES, AMPLITUDE MODULATION, GAS FLOW, HYPERSONIC CHARACTERISTICS, HYPERSONIC FLOW, MATHEMATICAL ANALYSIS, PRESSURE, SHOCK WAVES, THEORY

Distribution Statement : APPROVED FOR PUBLIC RELEASE