Asymmetric Vortex Wake Development on Missiles at High Angles of Attack

An analysis of recent wind-tunnel results is presented describing the influence of Mach number, Reynolds number, and body geometry on asymmetric vortex development and associated forces on slender missile configurations at high angles of attack. Experimental force and moment coefficients, load distributions, and surface-pressure distributions (steady and unsteady) are presented for several ogive and triconic nose configurations for angles of attack up to 90°, subsonic to low supersonic Mach numbers, and Reynolds numbers (based on body diameter) from 3.17X10 5 to 3.17X106. Asymmetric vortex locations and strengths, boundary-layer separation lines, and side-force coefficients are predicted using the unsteady cross-flow analogy and a discrete vorticity cross wake. Predictions of side force coefficients compare well with the force test data for angles of attack up to 40°. A a CN CY