Accession Number : AD0654450

Title :   AN APPROXIMATE ANALYSIS OF THE TWO-DIMENSIONAL, SUPERSONIC FLOW PAST A PLANE WALL WITH SUPER-CRITICAL HEAT ADDITION IN A NORMAL PLANE,

Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s) : Wollard,Henry W.

Report Date : MAR 1959

Pagination or Media Count : 71

Abstract : An analysis is performed to determine approximately the flow field and the normal forces acting for the two-dimensional, supersonic, zero angle-of-attack flow about a flat plate with super-critical heat addition (i.e., with thermal choking downstream) at a normal finite-height heater plane on one side of the flat plate. The results of the analysis have possible application to the design of an external thrust and/or lift producing device for airborne supersonic vehicles. Charts for the determination of the pertinent flow-field parameters and the normal force coefficients as a function of the rate of heat addition and free-stream Mach number, are presented for Mach numbers ranging from 2.0 to 7.0. (Author)

Descriptors :   (*SUPERSONIC FLOW, TWO DIMENSIONAL FLOW), FLOW FIELDS, NUMERICAL ANALYSIS, WALLS, HEAT, APPROXIMATION(MATHEMATICS), FLAT PLATE MODELS, THRUST, LIFT, HYPERSONIC FLOW

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE