Three dimensional shock wave/boundary layer interactions |
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Authors: | S Mowatt B Skews |
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Institution: | (1) G?rtnereiweg 3, 86938 Schondorf, Germany;(2) Institute of Aerodynamics and Flow Technology, Spacecraft Section, German Aerospace Center (DLR), Bunsenstra?e 10, 37073 G?ttingen, Germany;(3) Department Spacecraft, Institute of Aerodynamics and Flow Technology, Bunsenstra?e 10, 37073 G?ttingen, Germany;(4) Mechanical and Aerospace Engineering, Cornell University, 144 Upson Hall, 14853 Ithaca, NY, USA |
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Abstract: | An investigation into a three-dimensional, curved shock wave interacting with a three-dimensional, curved boundary layer on
a slender body is presented. Three different nose profiles mounted on a cylindrical body were tested in a supersonic wind
tunnel and numerically simulated by solving the Navier–Stokes equations. The conical and hemispherical nose profiles tested
were found to generate shock waves of sufficient strength to separate the boundary layer on the cylinder, while the shock
wave generated by the ogival profile did not separate the boundary layer. For the separated flow, separation was found to
occur predominantly on the windward side of the cylinder with the lee-side remaining shielded from the direct impact of the
incident shock wave. A thickening of the boundary layer on the lee-side of all the profiles was observed, and in the conical
and hemispherical cases this leads to the re-formation of the incident shock wave some distance away from the surface of the
cylinder. A complex reflection pattern off the shock wave/boundary layer interaction (SWBLI) was also identified for the separated
flow cases. For comparative purposes, an inviscid simulation was performed using the hemispherical profile. Significant differences
between the viscous and inviscid results were noted including the absence of a boundary layer leading to a simplified shock
wave reflection pattern forming. The behaviour of the incident shock wave on the lee-side of the cylinder was also affected
with the shock wave amalgamating on the surface of the cylinder instead of away from the surface as per the viscous case.
Test data from the wind tunnel identified two separation lines present on the cylindrical surface of the hemispherical SWBLI
generator. The pair of lines were not explicitly evident in the original CFD simulations run, but were later identified in
a high-resolution simulation. |
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