Three-dimensional Navier-Stokes simulations have been made for the transonic flow past a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes. Jet exhaust simulation is evaluated as are the Baldwin-Lomax (1978) and Goldberg (1986) turbulence models. Solutions are presented for Mach numbers of 0.80 and 0.94 at 0-deg angle of attack and a Reynolds number of 20 x 10 to the 6th. The numerical results are compared to wind-tunnel data. They show that including the jet exhaust in the calculations gives the most accurate solution near the nozzle exit. Also, the two turbulence models predict considerably different flow fields.


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    Title :

    Navier-Stokes simulation of transonic afterbody flows with jet exhaust



    Conference:

    AIAA Applied Aerodynamics Conference ; 1990 ; Portland, OR, United States


    Publication date :

    1990-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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