Numerical Simulation of High Incidence Flow over a Space-Plane at Supersonic Speed
High incidence flows about a Space-Plane under investigation at the National Aerospace Laboratory of Japan were numerically simulated at supersonic speed.The basic equations used here are the Reynolds-averaged thin-layer Navier-Stokes equations. The convective terms are evaluated by Roe’s flux difference splitting while the viscous terms are centrally differenced and treated separately from the convective terms.The resulting finite difference equations are integrated in time employing the LU-ADI factorization algorithm. The eddy-viscosity necessary for turbulent flow computation is evaluated by a modified Baldwin-Lomax model. The Space-Plane model consists of fuselage, strake-wing, and tail with angle of inclination of 30 deg. The computational grid around the model has an O-C topology with 110 streamwise, 103 circumferential, and 49 normal points. Computation was carried out at a Mach number of 1.5, angles of attack ranging from 0 to 45 deg, and a Reynolds number of 3 ×106. Strong shock waves as well as leading-edge vortices in the complicated flowfields are captured in detail by the present numerical simulation. Some of the computational results including force coefficients and surface pressure distributions were also compared with experimental data. These comparisons show that the numerical predictions are in good agreement with NAL’s supersonic wind tunnel test data.
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