Abstract
Viscous CFD computations are performed to predict the aerodynamic coefficients and flowfield for a missile with grid fins by using hybrid structure-unstructured grids. The computations are made at Mach numbers of 0.7 and 2.0. Full N-S equations are discretized into finite volume form and solved by an algorithm in LU-SGS. The comparisons between computation and experimental data are made, and the detailed flow structure near grid fin is shown and examined.
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