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Supersonic Aerodynamic Characteristics of a Maneuvering Canard-Controlled Missile with Fixed and Free-Rolling Tail Fins
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Abstract
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°.
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Citation
Blair, A., "Supersonic Aerodynamic Characteristics of a Maneuvering Canard-Controlled Missile with Fixed and Free-Rolling Tail Fins," SAE Technical Paper 901993, 1990, https://doi.org/10.4271/901993.Also In
References
- Corlett, William A. Howell, Dorothy T. Aerodynamic Characteristics at Mach 0.60 to 4.63 of Two Cruciform Missile Models, One Having Trapezoidal Wings with Canard Controls and the other Having Delta Wings with Tail Controls NASA TM X-2780 1973
- Burt, James R. Jr. The Effectiveness of Canards for Roll Control Tech. Rep. RD-77-8 U.S. Army Nov. 1976
- Blair, A. B., Jr. Allen, Jerry M. Hernandez, Gloria Effect of Tail-Fin Span on Stability and Control Characteristics of a Canard-Controlled Missile at Supersonic Mach Numbers NASA TP-2157 1983
- Sawyer, Wallace C. Jackson, Charlie M. Jr. Blair, A. B., Jr. Aerodynamic Technologies for the Next Generation of Missiles AIAA/ADPA Tactical Missile Conference April 27-28 1977 Gaithersburg, Maryland
- Blair, A. B., Jr. Wind Tunnel Investigation at Supersonic Speeds of a Remote-Controlled Canard Missile with a Free-Rolling Tail Brake Torque System NASA TP-2401 March 1985
- Jackson, C. M., Jr. Corlett, W. A. Monta, W. J. Description and Calibration of the Langley Unitary Plan Wind Tunnel NASA TP-1905 1981
- Allen, Jerry M. Shaw, David S. Sawyer, Wallace C. Remote Control Missile Model Test AGARD-CP-451 Flight Mechanics Panel Symposium May 9-12 1988 Ankara, Turkey