Accession Number : AD0767598

Title :   Internal Hypersonic Flow,

Corporate Author : POLYTECHNIC INST OF BROOKLYN N Y DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS

Personal Author(s) : Lin,T. C. ; Rubin,S. G.

Report Date : MAR 1973

Pagination or Media Count : 34

Abstract : Hypersonic flow in the entrance region of a cylindrical tube is analyzed. Both weak and strong viscous interactions are considered and the differences between internal and external flow with transverse curvature are discussed. For the weak interaction case, only the leading term or inviscid flow is considered. The rotational flow field is determined by a thin-shock-layer method. Comparisons are made with solutions obtained from the equivalence principle as well as with an exact numerical finite-difference integration. In the strong interaction region, the Karman-Polhausen integral method and the tangent-cone approximation are used to describe the boundary-layer flow and the streamwise pressure variation, respectively. The shock-wave location, the induced pressure field, the heat transfer and the displacement thickness are determined. It is found that transverse curvature leads to an adverse pressure gradient effect for internal flows. (Author)

Descriptors :   (*DUCTS, HYPERSONIC FLOW), PIPES, FLOW FIELDS, LAMINAR BOUNDARY LAYER, SHOCK WAVES, PRESSURE, SKIN FRICTION, NUMERICAL ANALYSIS

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE