A Method for Eliminating the Magnus Instability of a Finned Missile
AIR FORCE ARMAMENT LAB EGLIN AFB FL
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Subsonic one-degree-of-freedom and three-degrees-of-freedom wind tunnel tests were performed to determine whether N-vanes attached to a spinning, statically stable missile would eliminate the Magnus instabilities which can occur at high spin rates. The clean configuration missile that was tested had a large precession limit cycle of about 35 degrees amplitude. With N-vanes at 15 degrees, it was possible to eliminate the precession limit cycle. With the N-vanes at -15 degrees, the precession limit cycle was eliminated, and a nutation limit cycle of 25 degrees was created. The motion of the missile with and without N-vanes was photographed with a high speed camera. The angular data obtained were fit using the WOBBLE computer program to obtain the coefficients of pitching moment, pitch damping moment, and Magnus moment.
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