大机动飞行时旋翼翼型的动态失速模型

摘要

基于Beddoes-Leishman(B-L)动态失速模型,对前缘涡的分离条件和位置进行了修正,并采用了量纲为一的时间参数对前缘涡的累积和涡的移动在时间尺度上做更合理的建模,建立了涡位置和涡增量的关系,另外,改进了气流的再附着条件.算例表明采用修正后的B-L动态失速模型,能够有效地改善低马赫数下垂直力系数和力矩系数突变的临界点和峰值,而且改进了一般修正模型对气流再附着段的判断,有助于提高直升机在大机动飞行时旋翼大交变载荷的计算准确性.%A modified method based on the Beddoes-Leishman dynamic stall model is presented.Modifications include a new stall-onset criterion.The method improves the position and separation conditions of the leading edge vortex, and establishes the relationship between vortex’s position and accumulation through dimensionless time parameter.The reattachment boundary condition is also modified.The examples show an effective modification of the original model, which makes the model feasible while analyzing the high maneuvering flight condition of rotor.