北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (1): 60-63.

• 论文 • 上一篇    下一篇

双三角翼飞机气动力工程计算研究

黄俊1, 吴文正1, 武哲1, 柯贤德2   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 中国贵航集团飞机设计
  • 收稿日期:1998-06-24 出版日期:2000-01-31 发布日期:2010-09-27
  • 作者简介:黄俊(1964-),男,贵州黔西人,博士生,100083,北京.

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

HUANG Jun1, WU Wen-zheng1, WU Zhe1, KE Xian-de2   

  1. 1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics;
    2. Aircraft Design Institute of GAIG
  • Received:1998-06-24 Online:2000-01-31 Published:2010-09-27

摘要: 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.算法在某改型飞机方案设计中得到了成功的应用.

Abstract: 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.

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