Accession Number : AD0661545
Title : AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF MASS TRANSFER ON A WEDGE INDUCED LAMINAR SEPARATED BOUNDARY LAYER AT MACH 12.
Descriptive Note : Final rept.,
Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
Personal Author(s) : Ball,Karlheinz O. W.
Report Date : AUG 1967
Pagination or Media Count : 135
Abstract : The essential two-dimensionality of the flow was verified by comparing surface pressure and heat transfer results with small fences just covering the region of separation to results obtained without fences. The symmetry of the configuration also helped to minimize end effects. Surface pressure measurements at a wall to stagnation temperature ratio of 0.56 and heat transfer measurements at a wall to stagnation temperature ratio of 0.28 were made for aft-wedge deflection angles of 0, 5, 10, 15 and 20 degrees with variable suction obtained for each angle by varying the corner slot width. The extent of separation is shown to be extremely sensitive to suction. Removal of a small percentage of the boundary layer mass flow is sufficient to collapse the separated flow region for the present configuration. The effect of the suction is to remove the low momentum flow near the wall, thus enabling the remaining shear layer to negotiate a higher compression at reattachment. (Author)
Descriptors : (*LAMINAR BOUNDARY LAYER, *FLOW SEPARATION), (*MASS TRANSFER, HYPERSONIC FLOW), WEDGES, PRESSURE, MODEL TESTS, ANGLE OF ATTACK, SUCTION SLOTS, TWO DIMENSIONAL FLOW, STAGNATION POINT
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE