Accession Number : AD0707850

Title :   THEORETICAL INVESTIGATION OF SUPERSONIC LAMINAR SEPARATION IN A CONCAVE CORNER.

Descriptive Note : Technical rept.,

Corporate Author : CALIFORNIA UNIV BERKELEY DIV OF AERONAUTICAL SCIENCES

Personal Author(s) : Lu,Tsai An

Report Date : MAR 1970

Pagination or Media Count : 72

Abstract : Separation and reattachment of a supersonic laminar boundary layer in a concave corner, due to a free interaction process, are investigated by the method of integral relations. The proposed total enthalpy profile, which is represented as a polynomial in the streamwise velocity component, can satisfy all the physical conditions in the attached and separated regions. As a result, the effect of wall cooling together with suction can be studied within a single framework. The solution runs smoothly through the separation and reattachment points without any difficulties. The numerical results contain all the known physical characteristics associated with laminar separation. A critical point is found downstream of the reattachment point. This provides a criterion for determining the initial point of the interaction region. A new computational procedure is suggested after careful consideration of the nature of this critical point. The integral curve which leads away from the critical point will be matched with the curve originating at the initial interaction point ahead of the corner. In this way smooth continuation of the boundary layer displacement thickness is made possible. The present method appears to be simpler, more direct, and more versatile than many existing integral methods. Its extension to apply to a wider class of problems is under consideration. (Author)

Descriptors :   (*LAMINAR BOUNDARY LAYER, *FLOW SEPARATION), CURVED PROFILES, SUPERSONIC FLOW, INTEGRAL EQUATIONS, ENTHALPY, COANDA EFFECT, INTERACTIONS, CURVE FITTING

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE