双三角翼飞机气动力工程计算研究

Engineering Calculation Research of Aerodynamics for Aircraft with Double Delta Wing Configuration

双三角机翼比三角机翼气动布局具有更优越的升阻特性.飞机空气动力的工程计算是用数值方法寻求飞机最优设计方案的基础.采用基于面积比思想的半经验工程算法计算了双三角翼飞机的升力系数曲线斜率、零升阻力系数和诱导阻力因子.结果经风洞试验数据校验,精度完全能满足飞机方案设计要求.

The lift and drag characteristics of double delta wing configuration is more ascendant than that of delta wing configuration. To seek for the optimized aircraft design scheme with numerical methods is firmly bottomed upon the engineering calculation of aircraft aerodynamics. By using the semi experiential engineering arithmetic based on the ideology of area ratio, the slope of lift coefficient curve, the zero lift drag coefficient and the induced drag factor of double delta wing aircraft were calculated. Being compared and corrected by the data from wind tunnel tests, it is shown that the precision of calculated results quite meets the requirements of conceptual aircraft design. The arithmetic has been successfully adopted in the conceptual design of an aircraft version.