Accession Number : AD0678148

Title :   LEADING EDGE HEAT TRANSFER RATES IN THE REGION OF AN IMPINGING SHOCK,

Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CALIF

Personal Author(s) : Vasiliu,J.

Report Date : 10 FEB 1961

Pagination or Media Count : 43

Abstract : The three-dimensional problem of a bow-shock impingement on a leading edge is reduced to the two-dimensional case by considering the flow in a plane passing through the stagnation line of the leading edge and the forebody axis. A method of computing the bow shock-leading edge shock intersection on this plane is presented. The solution of this problem provides the inviscid flow parameters required in the calculation of the heat transfer rate in the shock impingement region. The method of estimating the shock strength required to cause separation is considered. For pure laminar separations at the stagnation line of the leading edge, under hypersonic flow conditions, a simple relation is obtained for the ratio of the average heat transfer rate in separated flow to the stagnation line heat transfer rate, and for the ratio of the corresponding coefficients. It is found that, this latter can attain a maximum value of two, for extremely high Mach numbers and sweep angles. The procedure for calculating accurately heat transfer rates for either fully laminar or fully turbulent separations is also given in detail. (Author)

Descriptors :   (*LEADING EDGES, *AERODYNAMIC HEATING), (*SHOCK WAVES, *HEAT TRANSFER), TWO DIMENSIONAL FLOW, STAGNATION POINT, HYPERSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, AIRFOILS, BOUNDARY LAYER TRANSITION, FLOW SEPARATION

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE