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Wind-tunnel Investigation at Mach Numbers from 0.50 to 1.29 of an Unswept, Tapered Wing of Aspect Ratio 2.67 with Leading- and Trailing-edge Flaps : Flaps Deflected in Combination

Louis S Stivers, Alexander W Malick

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Abstract

Report discusses the results of aerodynamic testing of an unswept, tapered wing with full-span, 25-percent-chord, plain, leading- and trailing-edge flaps at several angles of attack, leading-edge-flap deflection, and trailing-edge-flap deflection. This testing was done in an attempt to reduce the lift coefficients of the wings at moderate angles of attack and to provide more control for flight in the transonic Mach number range.

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What this paper is about

Report discusses the results of aerodynamic testing of an unswept, tapered wing with full-span, 25-percent-chord, plain, leading- and trailing-edge flaps at several angles of attack, leading-edge-flap deflection, and trailing-edge-flap deflection. This testing was done in an attempt to reduce the lift coefficients of the wings at moderate angles of attack and to provide more control for flight in the transonic Mach number range.

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Available abstract

Report discusses the results of aerodynamic testing of an unswept, tapered wing with full-span, 25-percent-chord, plain, leading- and trailing-edge flaps at several angles of attack, leading-edge-flap deflection, and trailing-edge-flap deflection. This testing was done in an attempt to reduce the lift coefficients of the wings at moderate angles of attack and to provide more control for flight in the transonic Mach number range.

Key concepts: Wing, Leading edge, Trailing edge, Wind tunnel, Deflection (physics), Structural engineering, Aerodynamics, Mach number

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Wind-tunnel Investigation at Mach Numbers from 0.50 to 1.29 of an Unswept, Tapered Wing of Aspect Ratio 2.67 with Leading- and Trailing-edge Flaps : Flaps Deflected in Combination — Research Paper | ScholarLens