Wind tunnel investigations were conducted on a generic cruciform canard-controlled missile configuration. The model featured fixed or free-rolling tail-fin afterbodies to provide an expanded aerodynamic data base with particular emphasis on alleviating large induced rolling moments and/or for providing canard roll control throughout the entire test angle-of-attack range. The tests were conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 2.50 to 3.50 at a constant Reynolds number per foot of 2.00 × 106. Selected test results are presented to show the effects of a fixed or free-rolling tail-fin afterbody on the static longitudinal and lateral-directional aerodynamic characteristics of a canard-controlled missile with pitch, yaw, and roll control at model roll angles of 0° and 45°.
Supersonic Aerodynamic Characteristics of a Maneuvering Canard-Controlled Missile with Fixed and Free-Rolling Tail Fins
Sae Technical Papers
Aerospace Technology Conference and Exposition ; 1990
1990-09-01
Conference paper
English
Aerodynamic Characteristics of a Canard-Controlled Missile with a Free-Spinning Tail
British Library Conference Proceedings | 1998
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