Computation and validation of asymmetric force and moment coefficients for lateral jet controlled supersonic missile

摘要

CFD predictions are compared with the wind-tunnel tests for a missile consisting of an ogive-nose cylindrical body, four wings and four in-line tail panels at nominal supersonic Mach numbers of 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 configurations 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. ^The 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 are discussed. ^(Author)