Accession Number : AD0608431

Title :   RAREFIED FLOW TRANSITION AT A LEADING EDGE,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE FLUID MECHANICS LAB

Personal Author(s) : Pan,Y. S. ; Probstein,Ronald F.

Report Date : OCT 1964

Pagination or Media Count : 92

Abstract : Rarefied flow near the leading edge of a flat plate is studied by using the Navier-Stokes equations as a model. By considering the structure of an oblique shock wave, new low density jump conditions are obtained which include the effects of inviscid curvature, thickness, and transport behind the shock. The latter effect leads to the concept of a 'velocity slip' (and temperature jump) behind a shock, analogous to that prevailing at a solid surface in a low density flow. One of the important results of the numerical calcula tions is that the local heat transfer rate at low Reynolds number can be greater than the free molecule value with a unit accommodation coefficient. This is shown to be consistent with near free molecule theories and with some experimental data. Correlation formulas for air of the surface heat transfer rate and pressure distribution are presented as a function of Reynolds number, Mach number, and surface temperature. (Author)

Descriptors :   (*AIRFOILS, HYPERSONIC FLOW), (*HYPERSONIC FLOW, FLAT PLATE MODELS), RAREFIED GAS DYNAMICS, SHOCK WAVES, MATHEMATICAL MODELS, PARTIAL DIFFERENTIAL EQUATIONS, NUMERICAL ANALYSIS, SLENDER BODIES, HEAT TRANSFER, REYNOLDS NUMBER, VISCOSITY, BOUNDARY LAYER, DENSITY, WAKE

Distribution Statement : APPROVED FOR PUBLIC RELEASE