The finite-volume Galerkin scheme for the unsteady three-dimensional Euler equations has been developed together with the unstructured adaptive mesh techniques for accurate analysis of the complicated inviscid compressible flow problems. Time evolution of the complicated flow phenomena has been solved using the time-dependent h-adaption (refinement and unrefinement) grid procedure on the unstructured triangular meshes in association with the quadtree/linked list data structures. Spatially high-order schemes are formulated by using the upwind TVD and the Flux-Corrected Transport (FCT) concept regarding the fluxes across the control volume edges.
Interaction of shock wave with a compression corner and interaction of that with an airfoil are studied. Also, in an axisymmetric shock tube, formation of exhaust jet excited by a blast wave expelled into an open quiescent ambience, and that expelled into an expansion tube are investigated. Calculated results are compared with the existing experimental data and holographic interferogram for assessment of the accuracy and efficiency of the computational method. The intricate transient flow structures of the unsteady supersonic exhaust jet associated with the shock waves, slipstreams, and spiral vortex have been resolved. For steady-state flow problems, the ONERA M6 wing and a fighter-type complete aircraft have been solved using the three-dimensional unstructured adaptive method. Used for initial grid generation is Delaunay triangulation and for adaptive mesh procedure the Bowyer's point insertion algorithm. The computed pressure distribution on the ONERA M6 wing has shown excellent comparison with the experimental data. The full aircraft aerodynamic data are also presented.
