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受成本和用户市场限制,轻型飞机通常采用相对简单的增升系统满足起降、爬升等极高的飞行安全要求,这些飞行状态涉及飞机的大迎角空气动力学特性.翼身接合部流动分离是影响大迎角性能的主要因素之一,因此,控制翼身接合部的流动分离,对改善轻型飞机的大迎角性能具有重要的工程应用价值.本文采用CFD和风洞试验方法,针对某轻型飞机增升构型开展翼根整流设计方法研究,给出了翼身接合部形状影响流动分离的物理机制,由前缘、展向和中后段构成的整流设计方法,整流参数及其三维参数化建模方法.采用该设计方法完成的某轻型飞机翼根整流设计方案,有效控制了翼根流动分离,改善了大迎角气动性能,有利于提高飞行安全性.研究结果已用于中国通用飞机公司某轻型飞机研制.
Due to cost and user market constraints, light aircraft usually use relatively simple lifting systems to meet the extremely high flight safety requirements such as take-off and landing, climb, etc. These flight conditions are related to the aircraft’s high angle of attack aerodynamics. Is one of the main factors affecting the performance at high angle of attack, therefore, controlling the flow separation of the wing joint has important engineering application value in improving the high angle of attack performance of light aircraft.In this paper, CFD and wind tunnel test methods, The research on the design method of wing-root rectification of light aircraft is carried out. The physical mechanism of the shape of the wing-body junction influencing the flow separation is given. The rectification design method is composed of leading edge, Parametric Modeling Method The design scheme of the wing root of a light aircraft that is completed by this design method effectively controls the wing root flow separation and improves the aerodynamic performance at high angles of attack and is conducive to the improvement of flight safety.The results have been used in China General Aircraft Corporation a light aircraft development.