A generalized close-coupled canard-wing configuration was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers of O.4O, 0.70, and 0.85 over an angle-of-attack range from -4° to 24°. Studies were made to determine the effects of canard vertical location, size, and deflection and wing leading-edge sweep on the longitudinal characteristics of the basic configuration. The two wings tested had thin symmetrical circular-arc airfoil sections with characteristically sharp leading edges swept at 60° and 44°. Two balances which allow separation of the canard-forebody contribution from the total forces and moments were used in this study. The data in this report supplement several earlier publications by the National Aeronautics and Space Administration.
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