Aerodynamics of Finned Missiles at High Angle of Attack

A theoretical and experimental investigation of the aerodynamics of finned missiles at high angle-of-attack is presented. The interaction of the body vortex wake region with the missile fins aiid the resulting effect on the forces and moments produced by the fins is studied. An aerodynamic flow model is derived for a circular cylinder body at high angle-of-attack in subsonic or supersonic flow. The forces and moments produced by the fins in subsonic flow are calculated by utilizing the present flow model and present lifting theory. The experimental investigation consists primarily of strain gage measurements on a finned body in subsonic flow. The present aerodynamic flow model is compared with experimental crossflow data and good agreement between theory and experiment is obtained. Extensive comparison is made between the present force and moment predictions and available experimental data. Generally good agreement is obtained between theory and experiment for all of the forces and moments. Results given particular attention are nonlinear rolling phenomena, induced side force, and fin Magnus.