Accession Number : AD0757062

Title :   Supersonic Boundary-Layer Separation and Reattachment-Finite Difference Solutions.

Descriptive Note : Final rept.,

Corporate Author : CINCINNATI UNIV OHIO DEPT OF AEROSPACE ENGINEERING

Personal Author(s) : Werle,Michael J. ; Polak,Arnold ; Bertke,Steven D.

Report Date : JAN 1973

Pagination or Media Count : 90

Abstract : The boundary-layer equations including the effects of interaction with a supersonic mainstream are solved using an implicit finite difference scheme. The free interaction process is studied extensively and favorable comparisons made with experimental data, expirical correlations, and analytical results. Solutions are presented for shockwave and compression ramp induced separations and reattachments for a Mach 3 mainstream at moderate and cold wall temperatures. Surprisingly little overheating is observed aft of reattachment. (Author)

Descriptors :   (*SUPERSONIC FLOW, BOUNDARY LAYER TRANSITION), LAMINAR FLOW, TURBULENCE, SHOCK WAVES, TWO DIMENSIONAL FLOW, THREE DIMENSIONAL FLOW, DIFFERENCE EQUATIONS, MATRICES(MATHEMATICS), GRAPHICS, HEAT TRANSFER, NUMERICAL ANALYSIS, FLOW FIELDS

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE