高效层流翼型设计及试验验证

doi:10.7527/S1000-6893.2022.26798

Abstract

Abstract: Laminar flow wing design technology is one of the important development directions of civil aircraft drag reduction design. A laminar airfoil design method for engineering applications is studied by using CST parameterization method and modern optimization algorithm. A laminar airfoil is designed based on the requirements of a laminar flow validator, and its laminar flow characteristics are verified by numerical calculation and high-speed wind tunnel test. The results show that the developed design method can realize the optimization design and reverse design of laminar airfoil, the laminar flow area on the optimized airfoil surface is significantly expanded and the lift-drag ratio is improved. The laminar flow section designed for the validator has more than 50% laminar flow area at the design point, and the drag reduction is more than 10% compared with the traditional wing section. The research results have certain reference value for laminar drag reduction design of civil and military high subsonic transport aircraft.

Key words: laminar flow wing, airfoil optimization, wind tunnel test, lift-drag ratio, transition

CLC Number:

V211.4

GENG Yansheng, AI Mengqi, WANG Wei, GENG Jianzhong, ZHAO Yan. Efficient design and experimental verification of laminar airfoil[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526798-526798.

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Efficient design and experimental verification of laminar airfoil

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