The aerodynamic heating of a swept stagnation line is examined in the high-altitude hypersonic flight regime where nonequilibrium dissociation/recombination in the boundary layer and finite surface catalysis effects are both important. Assuming a highly cooled (Tw/Ts<<1), we extend Fay and Riddells's well-known self-similar solution for nonequilibrium-dissociated flow to include the effects of sweepback and arbitrary surface catalycity. Specific results for heat transfer are presented for the same zero sweep baseline case that was used in Fay and Riddell's work. In the frozen gas-phase limit, it is found that the combined net effects of sweep angle Lambda wipe out the dissociation effects altogether beyond about Lambda is around 65 deg and thus eliminate the usual favorable effect of a noncatalytic wall in reducing nonequilibrium heat transfer. Regarding the gas-phase chemistry aspect, results for a completely noncatalytic wall show that notwithstanding the significant spanwise viscous dissipation heating effect on the dissociation rate the net sweep effect diminishes the gas-phase reaction effect to zero beyond Lambda is around 60 deg, analogously to the surface reaction case.


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    Title :

    Nonequilibrium-dissociated stagnation boundary-layer flow on an arbitrarily catalytic swept wing


    Additional title:

    Ungleichgewichtige Trennung einer Grenzschichtströmung entlang der Linie von Staupunkten eines Pfeilflügels mit willkürlichen katalytischen Oberflächeneffekten


    Contributors:
    Inger, G.R. (author)

    Published in:

    AIAA Journal ; 33 , 10 ; 1836-1841


    Publication date :

    1995


    Size :

    6 Seiten, 11 Bilder, 10 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English