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A method is presented for predicting fin forces and moments on missiles at high angle of attack in subsonic flow. The missile configuration is assumed to be composed of a circular cylinder body with planar cruciform fins of arbitrary leading and trailing edge sweep. Of primary interest is the effect of the symmetric body vortex wake on forces and moments produced by the fins. A previously developed flow model is used to calculate the flow field produced by the fins is used with a simple lifting theory to predict fin forces and moments. Typical lifting surface forces and moments predicted for arbitrary roll angle and roll rate are normal force, induced roll moment, and induced side force. Comparisons between theoretical results and experiments are given in the paper. (DePo)