
Accession Number : AD0478344
Title : CORRELATION FORMULAS FOR LAMINAR SHOCK TUBE BOUNDARY LAYER.
Descriptive Note : Technical documentary rept.,
Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF
Personal Author(s) : Mirels,H.
Report Date : DEC 1965
Pagination or Media Count : 38
Abstract : The laminar boundary layer behind a moving shock is studied. The major objective is to obtain improved correlation formulas (valid for large W, where W is the density ratio across the shock) and to simplify the procedure for obtaining boundary layer parameters. Numerical solutions for shear, heat transfer, and boundary layer thicknesses are presented for 1 < W < infinity, Prandtl Number = 0.67, 0.72 and 1.0 assuming constant rho mu rho = density and mu = viscosity and an ideal gas. Correlation formulas are obtained which agree with these numerical results to within fractions of a percent. Approximate corrections for variable rho mu and real gas effects are then introduced. Charts and tables are presented which describe boundary layers in air (Ms < or = 22) and argon (Ms < or = 10). (Author)
Descriptors : (*LAMINAR BOUNDARY LAYER, *SHOCK TUBES), SHOCK WAVES, DENSITY, SHEAR STRESSES, HEAT TRANSFER, THICKNESS, VISCOSITY, CORRECTIONS, HYPERSONIC FLOW, HYPERSONIC CHARACTERISTICS, SURFACE TEMPERATURE, AIR, ARGON, NUMERICAL ANALYSIS
Subject Categories : Test Facilities, Equipment and Methods
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE