Abstract
Computational Fluid Dynamics (CFD) predictions are compared with the wind-tunnel tests for a missile consisting of ogive-nose cylindrical body, four wings and four in-lined tail panels at nominal supersonic Mach Nos. 2, 3, 4 and 5 and at angles-of-attack ranging from 0 to 35 deg with and without a lateral jet thruster with thrust ratios of 1 and 4. Comparisons also include roll angles that lead to asymmetric missile configuration with the thruster jet. Excellent comparisons of the predicted normal force, side force, pitching moment, yawing moment and rolling moment coefficients with the measured data are shown. CFD computed flow-field is then utilized to show that the lateral thruster jet effectiveness diminishes as the jet thruster is gradually rolled towards the windward side of the missile. Flow-physics associated with this phenomenon and possible mechanisms to alleviate this effect is discussed.
Published Version
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