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.
Passive control of plume interference on slender axisymmetric bodies
Passive Vorrichtung zur Begrenzung der Störung der Umströmung von Raketen durch den Abgasstrahl
AIAA Journal ; 43 , 8 ; 1653-1662
2005
10 Seiten, 19 Bilder, 26 Quellen
Aufsatz (Zeitschrift)
Englisch
Rocket Plume Interference Effects on Slender Bodies at High Angles of Attack
British Library Conference Proceedings | 1999
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