Supersonic speeds are the rule for most modern missiles, which require a very high thrust level within a limited cross-sectional area. The aerodynamic designs in recent years, therefore, have focussed on understanding several problems associated with the plume expansion at high speeds and altitudes. These configurations generally have a highly underexpanded jet plume downstream of the exhaust nozzle exit, leading to considerable interactions between the exhaust plume and freestream near the tail of missile bodies. The boundary-layer separation and pitching and yawing moments that result from the interactions can have significant effects on missile stability and control. The physics of the plume-induced shock and separation, particularly at high plume to exit pressure ratios with and without shock-turbulent boundary-layer control methods, were studied using computational techniques. Mass-averaged Navier-Stokes equations with a two-equation turbulence model were solved by using a fully implicit finite volume scheme and time-marching algorithm. The control methodologies for shock interactions included a porous tail and a porous extension attached at the nozzle exit or trailing edge. The porous tail produced a weaker shock and fixed the shock position on the control surface. The effect of the porous extension on shock interactions was mainly to restrain the plume from strongly underexpanding during a change in flight conditions. These techniques could give an additional dimension to the design and control of supersonic missiles.


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    Title :

    Passive control of plume interference on slender axisymmetric bodies


    Additional title:

    Passive Vorrichtung zur Begrenzung der Störung der Umströmung von Raketen durch den Abgasstrahl


    Contributors:

    Published in:

    AIAA Journal ; 43 , 8 ; 1653-1662


    Publication date :

    2005


    Size :

    10 Seiten, 19 Bilder, 26 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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