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美国政府科技报告
>A LIMITED FLIGHT INVESTIGATION OF THE EFFECT OF THREE VORTEX-GENERATOR CONFIGURATIONS ON THE EFFECTIVENESS OF A PLAIN FLAP ON AN UNSWEPT WING
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A LIMITED FLIGHT INVESTIGATION OF THE EFFECT OF THREE VORTEX-GENERATOR CONFIGURATIONS ON THE EFFECTIVENESS OF A PLAIN FLAP ON AN UNSWEPT WING
Limited flight tests of a fighter airplane have been conducted to determine the effect of three vortex-generator configurations on the effectiveness of a plain flap. Vortex generators consisting of rectan¬gular airfoils mounted on the upper surface of the airplane wing at the 63-percent-chord station produced some increase in airplane lift coeffi¬cient at a given angle of attack, no increase in drag with flaps deflec¬ted 19°, and no increase in maximum normal-force coefficient. These vor¬tex generators mounted at the 75-percent-chord station in another test produced no increase in either airplane lift coefficient or maximum normal-force coefficient. A third generator configuration consisting of larger tapered airfoils mounted at the 63-percent-chord station of the airplane wing produced a considerable increase in lift coefficient for a given angle of attack at the 19° flap deflection in a glide but at the expense of Increased drag. The effect of these generators was equivalent to a further increase in flap deflection to 27°. Ho Improvement In flap effec¬tiveness was obtained with any of the generators tested for flaps deflec¬ted 45°.
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