Accession Number : AD0709473
Title : INFLUENCE OF CROSS FLOW ON TWO DIMENSIONAL SEPARATION.
Descriptive Note : Final scientific rept. 1 May 68-30 Apr 70,
Corporate Author : VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
Personal Author(s) : Leblanc,Roger ; Ginoux,Jean J.
Report Date : MAY 1970
Pagination or Media Count : 53
Abstract : A test technique using an axisymmetric model was successfully developed in order to study the effect of a small amount of cross flow on two dimensional laminar shock wave boundary layer interactions at a Mach number of 2.25. In the absence of cross flow the experimental results were in excellent agreement with Horton's theory developed for axisymmetric bodies. The effect of cross flow was to reduce the static pressures throughout the complete interaction region. It was also shown that two dimensional models with an aspect ratio of 2.5 could be used free of side effects to study the influence of a small amount of cross flow. (Author)
Descriptors : (*AERODYNAMIC CONTROL SURFACES, HYPERSONIC FLIGHT), (*TWO DIMENSIONAL FLOW, FLOW SEPARATION), LAMINAR BOUNDARY LAYER, SHOCK WAVES, INTERACTIONS, SWEPTBACK WINGS, JET ENGINE INLETS, WIND TUNNEL MODELS
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE