A method for accurately solving inviscid compressible flow in the subcritical and supercritical regimes about arbitrary geometries is presented. Computations are performed for the three test cases in two dimensions: first, transonic flow over NACA 0012 airfoil, second, supersonic flow over circular cylinder with "Inviscid Separation", and third cascade of 5%-chord circular arc airfoil flow simulation by fixed grid formulation and moving grid formulation respectively.
The method is based on the use of unstructured triangular meshes in two dimensions, and special emphasis is placed on the accuracy and efficiency of the solutions. High accuracy is achieved by careful scaling of the artificial dissipation terms, and by reformulation the inner and outer boundary conditions for both the convective and dissipative operators. A solution adaptive grid refinement strategy is presented which enhances the solution accuracy for complex flows. When coupled with an implicit residual averaging algorithm, this method (FVNS : Finite Volume Nodal Scheme) is shown to produce an efficient solver for flows about arbitrary configurations.
