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以势流理论为基础,采用工程方法并参考试验结果确定分离涡的起始分离位置,用不可压流涡段所产生扰动流场的线性迭加,计算涡分离流动流场。单独翼面、组合翼面标模和FC-1飞机计算结果与实验结果的对比表明,在失速迎角范围内,本文方法是一种有效的低速大迎角气动特性快速计算方法。
Based on the potential flow theory, the initial separation position of the separation vortex was determined by engineering method and with reference to the test results. The flow field of vortex separation flow was calculated by linear superposition of the perturbation flow field generated by incompressible vortex flow. The comparison between the calculation results and experimental results of single airfoil, combined airfoil and FC-1 shows that this method is an effective method for fast calculation of aerodynamic characteristics at high angles of attack and low angles of attack.