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首页> 美国政府科技报告 >LOW -SPEED PRESSURE –DISTRIBUTION INVESTIGATION OF A THIN-DELTA-WING-FUSELAGE MODEL WITH DOUBLE SLOTTED FLAP, EXTENDED DOUBLE SLOTTED FLAP, AND CANARD
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LOW -SPEED PRESSURE –DISTRIBUTION INVESTIGATION OF A THIN-DELTA-WING-FUSELAGE MODEL WITH DOUBLE SLOTTED FLAP, EXTENDED DOUBLE SLOTTED FLAP, AND CANARD

机译：具有双槽襟翼，扩展双槽襟翼和加拿大的薄三角翼模型的低压压力分布研究

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An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60° delta-wing—fuselage model equipped with double slotted and extended double slotted flaps. The effects of a canard on the loads of the wing with the extended-double slotted flap were also determined.. The wing had an aspect ratio of 2.31, taper ratio, of 0, sweep of 60° at the leading edge, and MCA 65AOO3 airfoil section parallel to the free-airstream direction.nResults of the investigation without' discussion, are presented in the form of longitudinal aerodynamic characteristics of the-extended-double-slotted-flap configuration and in the form of normal-force coef¬ficients and pitching-moment coefficients on the wing, vane, and flap;sample pressure plots;sample span load distributions;tabulated pressure coefficients;and tabulated section normal-force coefficients and section pitching moment coefficients.

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