SUMMARYAn incompressible Navier-Stokes solver using curvilinear body-ÿtted collocated grid has been developed to solve unconÿned ow past arbitrary two-dimensional body geometries. In this solver, the full Navier-Stokes equations have been solved numerically in the physical plane itself without using any transformation to the computational plane. For the proper coupling of pressure and velocity ÿeld on collocated grid, a new scheme, designated 'consistent ux reconstruction' (CFR) scheme, has been developed. In this scheme, the cell face centre velocities are obtained explicitly by solving the momentum equations at the centre of the cell faces. The velocities at the cell centres are also updated explicitly by solving the momentum equations at the cell centres. By resorting to such a fully explicit treatment considerable simpliÿcation has been achieved compared to earlier approaches. In the present investigation the solver has been applied to unconÿned ow past a square cylinder at zero and non-zero incidence at low and moderate Reynolds numbers and reasonably good agreement has been obtained with results available from literature.

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SummaryA first order panel method has been developed for calculating the incompressible potential flow about arbitrary three-dimensional wings. The method utilises a distribution of source and vorticity singularities on the mean camber surface of the wing and solves for the distribution by satisfying the boundary condition of zero normal flow at selected points on the surface of the wing. The method takes less computing time compared to other existing first order methods for the comparable numerical accuracy. This method can handle wings having cusped trailing edges and thin sections.