A zonal method is being developed for accurate and effective simulation of transonic turbulent flow past a complex configuration. In this method the flow field is first divided into a number of continuous subfields called blocks in such a way that each block is partialy bounded by a solid surface; hence, the solid source is mapped onto a rectangular boundary plane in the computational space for effective calculation of algebraic eddy viscosity. Then, in the solution process, each block is treated as an independnet flow problem modeled by the same set of time-dependent thin-layer Navier-Stokes equations with the interface boundary conditions updated at every time step. The zonal method has been investigated for the simulation of Mach 0.8 turbulent flow past a wing-fuselage configuration. Numerical results obtained with six block algebraic grids show that the computed shock location and pressure distribution on the Wing can be in good agreement with the experimental data if the block grids used are adaptive to important solution characteristics. It is concluded that the proposed zonal method is indeed a very promising approach to be developed further for complex configuration flow simulation.


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    Title :

    A zonal method for transonic turbulent flow past a wing-fuselage configuration


    Additional title:

    Eine Zonenmethode für transsonische, turbulente Strömungen hinter einer Flügel-Flugzeugrumpf-Anordnung


    Contributors:
    Yang, S.C. (author) / Hsu, C.C. (author) / Chyu, W.J. (author)


    Publication date :

    1990


    Size :

    9 Seiten, 9 Bilder, 15 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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