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采用数值计算方法对亚声速飞行器中常见的外露非升力杆状部件的整流剖面进行了研究,提出了一类新型的变参数椭圆剖面,其外形由二次曲线形状参数Rho和最大厚度位置确定。通过进行长细比在1.5至8之间的椭圆剖面、翼型剖面和变参数椭圆剖面的阻力、升力和结构特性对比分析,表明翼型剖面在长细比大于3时具有最小的阻力和最大的升力线斜率,进一步降低长细比可能出现负升力线斜率等现象,阻力也反而增加。标准椭圆阻力最大,而变参数椭圆剖面即使长细比降低至2仍有较好的阻力升力特性。综合对比表明采用前后Rho值为0.414/0.35的剖面阻力和升力线斜率较低,结构厚度和截面积相对翼型提高,作为整流剖面可能具有更好的气动与结构综合效率。
A new type of variable parameter elliptical profile is proposed by numerical calculation. The shape of the profile is determined by the conic shape parameter Rho and the maximum thickness position. By comparing the resistance, lift and structural characteristics of elliptical, slender and variable-parameter elliptical sections with a slenderness ratio of 1.5 to 8, it is shown that the airfoil section has the least resistance and maximum at a slenderness ratio of more than 3 The slope of the lift line to further reduce the slenderness may occur negative lift line slope and other phenomena, the resistance also increased. The standard elliptical resistance is the largest, while the variable parameter elliptical profile has better resistance lift characteristics even if the slenderness ratio is reduced to two. The comprehensive comparison shows that the slope resistance and lifting line with Rho value of 0.414 / 0.35 before and after use are lower, and the thickness and cross-sectional area of the structure are increased relative to the airfoil. As a result, the rectifying section may have better aerodynamic and structural efficiency.