The three-dimensional crossing shock wave/turbulent-boundary-layer interaction caused by an asymmetric 7 × 11-deg double fin with incoming Mach number 3.95 was simulated using the Reynolds-averaged Navier-Stokes equations with a full Reynolds stress equation turbulence model. An implicit approximate factorization method is used for the temporal integration. Roe's scheme is used for evaluation of the convective terms of the mean flow and Reynolds stress equations with a third-order MUSCL-type differencing. The computed surface pressure is in good agreement with the experiment. The computed heat transfer coefficient shows a modest improvement compared with previous results obtained using the k-∈ model with Chien's low-Reynolds-number correction. Both computations of the heat transfer display significant deviations from experiment. Tests of the grid refinement, different upstream boundary-layer profiles, and different isothermal wall temperature also are presented.
ASJC Scopus subject areas
- Aerospace Engineering