The results of an investigation of a model simulating a missile with extensible control surfaces and small-span fins are presented. Normal-force, axial-force, and pitching-moment coefficients based on body cross-sectional area and diameter are given for various control deflections up to a maximum of 30°. Sufficient information is presented to permit an evaluation of the maneuvering performance of the airframe at supersonic Mach numbers up to 3. The importance of bodylift is illustrated by the fact that as the Mach number increases, the airframe turning performance compares more and more favorably with that of an equivalent body fitted with variable-incidence wings.
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