Assessment of Wind Tunnel and CFD Transonic Base Pressure Using Flight Data

2007 
The transonic base pressure distributions on a winged re-entry vehicle configuration derived from wind tunnel tests and CFD analyses are compared to flight data from the High Speed Flight Demonstration Phase II test. Results show that wind tunnel forebody axial force data agree well with the flight test data, but the base pressures differ. For a wind tunnel model supported by a straight sting, base pressure correction using ventral model support data was found to be effective when the model was located far upstream of the roll pod. The base pressure obtained by CFD depends greatly on the number of grid points used in the base flow region, and it is shown that dense grids are able to reproduce the effect of the existence of the support sting despite the use of a classical turbulence model.
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