Accession Number : AD0756890
Title : Transition Run-Out Calculations for a Compressible Boundary Layer with Wall Cooling.
Descriptive Note : Final rept. 3 Jan-4 Oct 72,
Corporate Author : AERONAUTICAL RESEARCH ASSOCIATES OF PRINCETON INC N J
Personal Author(s) : Yates,John E. ; Donaldson,Coleman duP.
Report Date : OCT 1972
Pagination or Media Count : 42
Abstract : -183F33615-72-C-1350AF-1366136606AFFDLTR-72-123(*boundary layer transition, mathematical analysis), turbulence, equations of motion, reynolds number, temperature, velocity, flow fields, mathematical modelsprofiles, temperature, profiles, velocityAn analytic model developed for the study of transition in a compressible boundary layer is used to make comprehensive transition run-out calculations for Mach numbers between 0 and 12 and wall temperature ratios between 0.05 and 1.2. Calculated results for the transition Reynolds number and the minimum critical Reynolds number for a growing boundary layer are compared with previous calculations for a frozen uniform parallel flow and with experimental transition results. The theory predicts the beginning of transition at the outer edge of the boundary layer for hypersonic Mach numbers, in agreement with experimental findings. (Author Modified Abstract)
Descriptors : (*BOUNDARY LAYER TRANSITION, MATHEMATICAL ANALYSIS), TURBULENCE, EQUATIONS OF MOTION, REYNOLDS NUMBER, TEMPERATURE, VELOCITY, FLOW FIELDS, MATHEMATICAL MODELS
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE