Similar Solutions of the Attached and Separated Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH WRIGHT-PATERSON AFB
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The development of governing equations and tabulation of similar solutions to the two-dimensional, laminar, compressible boundary layer with heat transfer are presented. Similar velocity and temperature profiles and global quantities such as displacement thickness, momentum thickness, form factor, etc., are presented for 116 pressure gradient-heat transfer combinations. Surface temperatures for these cases range from absolute zero S0 - 1 to twice the free stream stagnation temperature S0 1, while the streamwise pressure gradient varies from values corresponding to maximum reversed flow beta-0.36 to those of extremely accelerated flows beta 20. Results are presented at regular intervals of the parameters S0 and beta, allowing for straight-forward comparisons between cases. Five decimal place accuracy is maintained for all results.