Investigation of Supersonic Flow Over a Rearward Facing Step
Author : Michael Wen-Shean Su
Publisher :
Page : 142 pages
File Size : 30,53 MB
Release : 1970
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Author : Michael Wen-Shean Su
Publisher :
Page : 142 pages
File Size : 30,53 MB
Release : 1970
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Author : Jain-Ming Wu
Publisher :
Page : 10 pages
File Size : 12,40 MB
Release : 1970
Category : Aerodynamics, Supersonic
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Author : Harry Allen Berman
Publisher :
Page : 180 pages
File Size : 36,19 MB
Release : 1982
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Author : Stephen Corda
Publisher :
Page : 218 pages
File Size : 26,74 MB
Release : 1982
Category : Airplanes
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Author : Albert L. Waters
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Page : 77 pages
File Size : 10,82 MB
Release : 1969
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The supersonic flow field over a rearward facing step was studied with a schlieren system. The effect of Mach number variation, step height variation, and total pressure variation on the expansion fan angle, lip shock angle, flow turning angle, reattachment point, and reattachment shock angle was determined. Schlieren photographs of the flow at Mach number 2.7 to 3.1, step heights of 1/4 to 3/4 in, and total pressures of 60 to 95 psia are presented. It was found that the relatively small changes in Mach number had the smallest effect on the flow field and that changing the step height had the greatest effect on the flow field. The flow turning angle was sensitive to all three variables.
Author : Albert L. Waters (CAPT, USAF.)
Publisher :
Page : 64 pages
File Size : 11,18 MB
Release : 1969
Category : Aerodynamics, Supersonic
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Author : Steven Mark Sahm
Publisher :
Page : 254 pages
File Size : 40,19 MB
Release : 1985
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Author : Odus R. Burggraf
Publisher :
Page : 56 pages
File Size : 39,24 MB
Release : 1970
Category :
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The problem of laminar separated flow over a backward-facing step is solved numerically for the limiting case of infinite Reynolds number. The flow model adopted is that deduced by Batchelor for incompressible flow: an inviscid rotational eddy confined within the recirculation portion of the separated shear layer. It is argued that the reattachment process is essentially inviscid in the limit R approaches infinity, and the flow field in the reattachment zone is computed on this basis. The computed results support Chapman's model of the reattachment process as the correct limit case, to second-order accuracy, as the flow angle entering the reattachment zone approaches zero. For the recirculation zone, the boundary-layer equations are simplified by assuming a constant pressure eddy. The Dorodnitsyn transformation is applied and numerical solutions obtained using an implicit finite-difference scheme. The solutions are carried out from station-to-station in the direction of flow over a complete cycle of recirculation. Iteration yields the unique value of the vorticity in the inviscid layer upstream of separation, including the effects of corner expansion and recirculation on the development of the separated shear layer. (Author).
Author : Howard Edwin Smith
Publisher :
Page : 236 pages
File Size : 45,93 MB
Release : 1969
Category : Aerodynamics, Supersonic
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Author : Matthew J. Warfield
Publisher :
Page : pages
File Size : 30,75 MB
Release : 1995
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ISBN :