Abstract
Pitch- and roll-damping test mechanisms were developed for obtaining stability characteristics of high fineness ratio missiles at angles of attack up to 90 deg. Wind-tunnel tests were conducted on two missile configurations at Mach numbers 0.22 through 2.5. Mechanism evaluation tests showed that strut interference was not appreciable. The pitch-damping derivatives were found to be highly nonlinear functions of angle of attack, and the roll-damping and Magnus characteristics were very nonlinear with spin rate'at high angles of attack and low Mach numbers. Large and erratic variations in side force and yawing moment with angle of attack and high autorotation characteristics also were found at the low Mach numbers.
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