The objective of this investigation is to numerically evaluate effects of a reaction control (divert) jet on the aerodynamic performance of a generic interceptor missile operating at supersonic flight conditions. The effects investigated include transient operation, external chemical reactions and combustion, and geometric scale, specifically full scale versus subscale. Parametric computational fluid dynamic solutions are obtained at altitude conditions corresponding to 19.7 km for the following scenarios: 1) steady-state conditions with the lateral control jet turned off; 2) steady-state conditions with the lateral control jet turned on; 3) steady-state conditions with the lateral control jet turned off, one-tenth subscale geometry; 4) steady-state conditions with the lateral control jet turned on, one-tenth subscale geometry; 5) transient jet startup conditions; 6) transient jet shutdown conditions; 7) steady-state, finite-rate chemistry; and 8) steady-state, chemically frozen calculations. Specifically, all chemical reactions are "turned off." Vehicle forces and moments are assessed for each solution by integrating the computed surface pressures and viscous shear stresses on the missile surfaces. These results are used to determine the influence of the jet interaction effects on the transient, external combustion, and geometric scale and associated effects on the aerodynamic performance of the missile. The analysis predicts strong transient influences, small external combustion influences, and very small full-scale vs one-tenth subscale geometry effects on the integrated normal force and pitching moment.
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