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A compressible non-body conformal grid method is presented. The method is designed to simulate a large variety of subsonic compressible flows with complex geometries. A hybrid implicit-explicit timediscretization scheme is chosen. The diagonal viscous terms are treated implicitly and all other terms including the convective terms and cross-terms are treated explicitly using a low-storage, 3 rd-Order Runge-Kutta scheme. A mixed second-order central difference-QUICK scheme has been used which allows us to precisely control the numerical damping. A ghostcell approach is employed in conjunction with a bilinear interpolation scheme so as to satisfy the boundary conditions on the immersed boundaries while preserving second-order accuracy. Numerical results are validated by comparing against experimental data and other established simulation results.

The formation of the tip-vortex from a rectangular NACA 2415 wing-tip at a chord Reynolds number of 10000 has been simulated. The simulations employ a parallelized compressible large-eddy simulation (LES) solver that has been developed to simulate wing and rotor tip-flows. The solver employs an immersed-boundary technique in conjunction with a curvilinear structured grid and the dynamic model is used to model the subgrid-scale (SGS) stress terms. A d etailed discussion of the tip-vortex formation and evolution in the near wake is presented.

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