Accession Number : AD0696293

Title :   THE NON-LINEAR REFRACTION OF SHOCK WAVES BY UPSTREAM DISTURBANCES IN STEADY SUPERSONIC FLOW,

Corporate Author : BOEING SCIENTIFIC RESEARCH LABS SEATTLE WASH FLIGHT SCIENCES LAB

Personal Author(s) : Weinbaum,Sheldon ; Goldburg,Arnold

Report Date : SEP 1969

Pagination or Media Count : 63

Abstract : The general problem studied is the propagation of an oblique shock wave through a two-dimensional, steady, non-uniform oncoming flow. A higher order theory is developed to treat the refraction of the incident oblique shock wave by irrotational or rotational disturbances of arbitrary amplitude provided the flow is supersonic behind the shock. A unique feature of the analysis is the formulation of the flow equations on the downstream side of the shock wave. Analytical and numerical solutions to the basic shock refraction relation are presented for a broad range of flows in which the principal interaction occurs with disturbances generated upstream of the shock. These solutions include the passage of a weak oblique shock wave through: a supersonic shear layer, a converging or diverging flow, a pure pressure disturbance, Prandtl-Meyer expansions of the same and opposite family, an isentropic non-simple wave region, and a constant pressure rotational flow. The comparison between analytic and numerical results is very satisfactory. (Author)

Descriptors :   (*SHOCK WAVES, REFRACTION), (*SUPERSONIC FLOW, SHOCK WAVES), NONLINEAR SYSTEMS, TURBULENCE, PRESSURE, EQUATIONS OF MOTION, PROPAGATION, TWO DIMENSIONAL FLOW, NUMERICAL ANALYSIS

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE