Influence of Cross Flow on Two Dimensional Separation
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).
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80 mm Hg absence of cross AIAA amount of cross angular velocity aspect ratio axisymmetric bodies axisymmetric flows Basic pressure distribution boundary layer interactions boundary layer separation Centrifugal effect cross flow due cylinder flare model dary diameter dimensional laminar shock dimensional models effect of cross equations Flare angles flare cylinder model flare location free of side free stream static GIN0UX Ginoux hypersonic infinite span Influence of cross inner body inviscid Klineberg's method laminar boundary layer laminar flow laminar or transitional laminar shock wave leading edge Lees and Reeves lU and 15 Mach number number of 2.25 pressure distributions measured Pressure measurements ratio of 2.5 reattachment reference pressure scanivalve Security classification unclassified Shadowgraph shock absorbers shock wave boundary shown in fig small amount spinning model static pressure distribution stream static pressure test section transducer tunnel stagnation pressure vanes viscous VKI TN wave boundary layer wind tunnel