
Accession Number : AD0800242
Title : HYPERSONIC VISCOUS FLOW PAST A FLAT DELTA WING AT MODERATE ANGLE OF ATTACK.
Descriptive Note : Technical rept. Apr 65Jul 66,
Corporate Author : CINCINNATI UNIV OH DEPT OF AEROSPACE ENGINEERING
Personal Author(s) : Polak, Arnold ; Li, Ting Y.
Report Date : SEP 1966
Pagination or Media Count : 45
Abstract : This is a study of the threedimensional boundary layer over the windward side of a flat delta wing in hypersonic flow at a moderate angle of attack. The interaction between the inviscid and the viscous flow region is analyzed, and its effect is taken into account. The theory is developed for thin flat delta wings with the shock detached from the leading edges and attached at the apex. The inviscid solution based on the Newtonianconical flow theory of MessiterHida has been matched to the threedimensional boundary layer solution over the wing. The transverse velocity component normal to the conical ray is small and a perturbation method leads to a system of ordinary differential equations. The solution of these equations together with the tangentcone method is used to study the viscousinviscid interaction. The results are applied to calculate the streamline pattern, induced pressure, skin drag and heat transfer over the wing surface. The present theory is in general agreement with the available experimental data. (Author)
Descriptors : (*DELTA WINGS, HYPERSONIC CHARACTERISTICS), (*HYPERSONIC FLOW, MATHEMATICAL MODELS), FLAT PLATE MODELS, SURFACE PROPERTIES, THREE DIMENSIONAL FLOW, BOUNDARY LAYER, ENTHALPY, PRESSURE, DRAG, PERTURBATION THEORY, DIFFERENTIAL EQUATIONS, HEAT TRANSFER, SHOCK WAVES, LEADING EDGES, SKIN FRICTION.
Subject Categories : Numerical Mathematics
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE