AbstractSmall disturbance equations for the downstream flow of a transonic aircraft are derived from the steady, viscous, compressible Reynolds-averaged Navier–Stokes equations. These equations are then simplified further for the relevant case of high Reynolds numbers. The given analysis appears not to be trivial, implying a mild form of ambiguity, leading to two acceptable strategies to solve the equations. The physical mechanisms that play a role in vortex decay and the consequent downstream transition of crossflow kinetic energy into viscous/thermodynamic streamwise momentum deficit are identified. The case of discrete trailing vortices having a distinct vortex core is briefly discussed. Four invariant vorticity moments playing a role in the wake roll-up process are re-derived.


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    Title :

    The downstream flow of a transonic aircraft: a small disturbance, high Reynolds number analysis


    Contributors:

    Published in:

    Publication date :

    2007-11-06


    Size :

    12 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Reynolds Number Effects in Transonic Flow

    A. Elsenaar / T. W. Binion / E. Stanewsky et al. | NTIS | 1989


    Reynolds number effects in transonic flow

    Elsenaar, A. ;Binion, Travis W. ;Stanewsky, E. | TIBKAT | 1988