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Wind-Tunnel Measurements of Wing-Canard Interference and a Comparison with Various Theories
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1981 by SAE International in United States
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CANARD-CONFIGURED AIRCRAFT DESIGNS have played a historic role in aeronautical research. However, only in the past decade or two has a canard been incorporated into a significant number of aircraft designs. Powered flight began with the Wright Flyer, which was a canard-configured aircraft. Unfortunately, however, that aircraft was longitudinally unstable and the misconception arose that all canard aircraft would be unstable in pitch, irrespective of the placement of the center of gravity. In the early years of aircraft development, the canard concept was dropped in favor of conventional tailaft designs. It was not until the 1960s that canards were again seriously considered for several high-speed, designs. For example, in the United States’ supersonic transport program, a canard was initially considered; because of several problems with aerodynamic interference, however, the idea was abandoned. For example, the canard wake passed around the vertical stabilizer and resulted in erratic directional behavior. Canard tip vortices
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CitationFeistel, T., Corsiglia, V., and Levin, D., "Wind-Tunnel Measurements of Wing-Canard Interference and a Comparison with Various Theories," SAE Technical Paper 810575, 1981, https://doi.org/10.4271/810575.
- RutanBurt, “Tale of the Three EZ's.” Sport Aviation, Vol. 29, No. 2, Feb. 1980.
- MiltonD. McLaughlin, “Calculations and Comparisons with an Ideal Minimum of Trimmed Drag for Conventional and Canard Configurations Having Various Levels of Static Stability.” NASA TN D-8391, May 1977.
- LaitoneE. V., “Prandtl's Biplane Theory Applied to Canard and Tandem Aircraft.” J. Aircraft, Vol. 17, No. 4, Apr. 1980, pp. 233-237.
- WolkovitchJulian, “Subsonic V/STOL Aircraft Configurations with Tandem Wings.” J. Aircraft, Vol. 16, No. 9, Sept. 1979, pp. 605-611.
- DurandW. F.ed, “Aerodynamic Theory.” Vol. II, Reprinted by Dover, New York, 1963.
- RobertB. Addoms and FrankW. Spald, “Aerodynamic Design of High-Performance Biplane Wings.” J. Aircraft, Vol. 12, No. 8, Aug. 1975.
- RobertJ. McGhee, WilliamD. Beasley, and DanM. Somers, “Low-Speed Aerodynamic Characteristics of a 13-Percent Thick Airfoil Section Designed for General Aviation Applications.” NASA TM X-72697, May 1977.
- RobertJ. McGhee and WilliamD. Beasley, “Low-Speed Aerodynamic Characteristics of a 17-Percent Thick Airfoil Section Designed for General Aviation Applications.” NASA TN D-7428, 1973.
- RobertT. Jones and CohenDoris, “High Speed Wing Theory.” Princeton Aeronautical Paperbacks, No. 6, Princeton University Press, 1960.