A holographic interferometry study of an axisymmetric shock-wave/boundary-layer strong interaction flow
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An experimental study of the axisymmetric shock-wave/ turbulent boundary-layer strong-interaction flow generated in the vicinity of a cylinder-cone intersection has been conducted. The present data are useful in the documentation and understanding of compressible turbulent strong-interaction flows, and are part of a more general effort to improve turbulence modeling for compressible two- and three- dimensional strong viscous/inviscid interactions. The nominal free-stream Mach number was 2.85. Tunnel total pressures of 1.7 and 3.4 atm provided Reynolds number values of 18 x 106 and 36 x 106 based on model length. Three cone angles (12.5 [degrees], 20 [degrees], and 30 [degrees]) were studied giving negligible, incipient, and large scale flow separation respectively. The initial cylinder boundary layer upstream of the interaction had a boundary-layer thickness of 1.0 cm. The subsonic layer of the cylinder boundary layer was quite thin, and in all cases, the shock wave penetrated a significant portion of the boundary layer. Owing to the thickness of the cylinder boundary layer, considerable structural detail was resolved for the three shock-wave/boundary-layer interaction cases considered. The primary emphasis in this study was on the application of the holographic interferometry technique to these flow cases. The density field was deduced from an interferometric analysis based on the Abel transform. Supporting data were obtained using a 2-D laser velocimeter, as well as mean wall pressure and oil flow measurements. The attached flow case was observed.to be steady, while the separated cases exhibited shock unsteadiness. Comparisons with Navier-Stokes computations using a two-equation turbulence model are presented. The study illustrates the utility of holographic interferometry for detailed instantaneous flow-field characterization and provides documented data useful in the evaluation of computational schemes.
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