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Numerical Simulation of Transient Jet Interaction on a Generic Supersonic Missile with Fins,

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The objective of this investigation is to evaluate the transient effects of a reaction control jet on the aerodynamic performance of a generic interceptor missile, Three dimensional computations of the highly turbulent flow field produced by a pulsed, lateral jet control thruster and the interaction of this jet with the supersonic free stream and missile boundary layer were completed for different altitudes and thruster conditions. A generic supersonic missile interceptor configuration consisting of a long, slender body LID14.1 containing fixed dorsal and tail fins was used in this study. Parametric computational fluid dynamic CFD solutions were obtained at two altitudes of 64.5 kft 19.7 km and 115 kft 35.1 km. Computation of the flow field behaviors at each altitude were completed for the following assumptions 1 steady state conditions, lateral control jet turned off, 2 steady-state conditions, lateral control jet turned on, 3 transient jet startup simulation, and 4 transient jet shutdown simulation. A thermally perfect gas gamma1.4 was assumed for the Mach number 5 free stream and the Mach number 3 lateral jet. Vehicle forces and moments were obtained for each solution by integrating the surface pressures and viscous shear stresses computed on the missile surfaces. These results are applied to assess the influence of the jet interaction JI effects on the transient aerodynamic performance of the missile. The analysis indicates that strong transient influence is predicted in the integrated normal force and pitching moment. These effects may be influenced by the dorsal fin interaction with the jet interaction JI region.

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  • Antimissile Defense Systems
  • Fluid Mechanics

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