气动力计算的积分技术讨论  

Discussion of integral technique for aerodynamics calculation

作　　者：刘杰[1] 朱自强[1] 陈泽民[1] 吴宗成[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2006年第2期139-143,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(10472013);航空科学基金资助项目(04A51044)

摘　　要：讨论了“尾迹面积分法”的气动力计算方法及其改进技术.基于欧拉方程求解流场,通过对飞行器以外的一个控制体采用动量定理而得,是传统远场积分法的改进.在飞行器所在流场的下游一垂直于来流速度的截面上进行积分计算,得到升力、诱导阻力、激波阻力和总阻力.这种方法的优点是有利于外形复杂物体的气动力积分计算,并可将总阻力按产生的物理机理进行分解,以使设计师对飞行器的气动特点有更为明确的了解.详细讨论了影响这种方法计算精度和效率的多种因素及解决途径.各种数值模拟结果证明了该方法和改进技术的正确性和实用性.A method called wake integration for the aerodynamics evaluation was discussed. Based on Euler equations to get the fluid field solution, this method applies the momentum theorem to a control volume that encloses an aircraft and it is improved from the traditional far field integration method. By doing integral computation on the wake surface that is down from the aircraft and vertical to the velocity of far field, it can get the lift, induced drag, wave drag and the total drag. This method is advantaged to the aerodynamics calculation for the aircraft having the complicated configuration and it can decompose the total drag by physical causes. Consequently the designer can be aware of more details about the aerodynamics of the configuration in the design. Some methods to improve the accuracy and efficiency of wake integration were discussed. The results of the computation demonstrate that the method and improved technique are correct and useful in the aircraft design.

关 键 词：气动力计算 尾迹面积分 表面积分 阻力分解 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]