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Low-Speed Aerodynamic Characteristics of a Model Having a 42 Deg Swept Low Wing with a Supercritical Airfoil, Double-Slotted Flaps, and a T-Tail

机译:具有42度扫掠低翼与超临界翼型,双槽襟翼和T型尾翼的模型的低速空气动力学特性

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摘要

A low speed wind tunnel test was conducted in the Langley V/STOL tunnel to determine the static longitudinal and lateral stability characteristics of a general research model which simulated an advance configuration for a commercial transport airplane with a T tail. The model had a 42 deg swept, aspect ratio 6.78 wing with a supercritical airfoil and a high lift system which consisted of a leading edge slat and a double slotted flap. Various slat and flap deflection combinations represented clean, take off, and landing configurations. Effects on the longitudinal and lateral aerodynamic characteristics were determined for two flow through, simulated engine nacelles located on the sides of the fuselage near the rear of the model.

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