摘 要：为改善某型水陆两栖飞机的起降性能，提高其抗浪能力，需设计高性能吹气襟翼以满足其性能要求。本文在国内外已有的吹气襟翼研究基础上，结合飞机气动综合优化设计框架及计算流体力学的优势，以设计出高气动效率及工程实用性的吹气襟翼方案作为设计目标，对吹气襟翼的基本形式、吹气缝道位置及喷缝参数等进行综合优化设计，最终通过风洞试验来验证优化设计方案的有效性。从分析及验证结果来看，通过本优化设计方法所设计的吹气襟翼，能在使用相同吹气动量系数的条件下，明显推迟了襟翼上的气流分离，实现最大升力系数20%左右的提升，显著提升了吹气襟翼的气动效率，为进一步实现吹气襟翼的工程应用奠定了基础。
Abstract: In order to improve the take-off and landing performance of the large amphibian，enhance its anti-wave capacity, the jet flap with high-performance is designed to meet their performance requirements. In this paper, based on the existing jet flap research results, combined with the aircraft aerodynamic optimization design framework and CFD numerical simulation methods to design a high aerodynamic efficiency and engineering useable jet flap solutions as a design target, By research the basic form of jet flaps, gas blowing position and optimize the design parameters and so on, end-to proving the optimal design program by wind tunnel tests. From the analysis and verification results, use these optimization methods to design jet flap, in use the same momentum coefficient blowing conditions such flow separation flap has been significantly delayed and achieve maximum lift coefficient of about 20% upgrade, significantly enhance the aerodynamic efficiency of the jet flap, and laid the foundation for the jet flap engineering applications.
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