23 Dec

Shock Wave/Turbulent Boundary Layer (SWTBL) Study Presented at AIAA Aviation 2014

Experimental studies have been conducted to obtain detailed heat transfer and pressure measurements in regions of shock wave/turbulent boundary layer interaction over cone/flare and hollow cylinder/flare configurations in high Reynolds number hypervelocity flows for comparison with computations with CFD codes employing a range of turbulence models. These studies were conducted at a series of Mach numbers between 5 and 10, in cold flows and in flows with duplicated flight velocities in fully turbulent flows. Schlieren photographs of the interaction regions and detailed surface pressure and heat transfer measurements were made through the separated interaction regions as well as upstream and downstream of the interactions which provide well-defined boundary conditions for a range of Reynolds numbers under cold freestream flow ( Tw=100 R) and conditions for total enthalpies duplicating flight. The large scale of the models used in these experiments enabled us to obtain measurements in fully turbulent flows with the length of turbulent flow up to 1,000 boundary layer thicknesses downstream of the beginning of untripped transition. The surface measurements obtained in these studies together with Schlieren and interferometry measurements of the regions of shock wave/boundary layer interaction were originally assembled to provide data sets for “blind” code validation studies. Both sets of measurements have been compared with calculations with the major codes using a number of turbulence models by knowledgeable researchers and this information is available via links below as are tabulations of the measurements presented in the paper.

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