Presented at the STAR Global Conference 2012.
One of the difficulties in performing hypersonic aerodynamic performance prediction is determining accurate lift and drag profiles.
This presentation illustrates the comparison of wind tunnel data for a 70° sweep slab delta wing to STAR-CCM+ predictions at various hypersonic Mach numbers. These comparisons include pressure distribution on the surface, heat transfer coefficients and forces / moments on the model. The Mach numbers investigated are Mach 6.8, 9.6 and 18.4 at angles of attack from -2°- 45°.
M. H. Bertram, P. E. Everhart ‘An experimental study of the pressure and heat-transfer distribution on a 70° sweep slab delta wing in hypersonic flow’, NASA Technical Report R-153, Langley Research Center, 1963.