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可变翼型在提高升力、减振降噪、延缓动态失速等方面具有显著效果,已受到越来越多的关注.但是,目前还缺乏准确高效的可变翼型动态失速气动模型.本文将动态失速引起的环量加入到二维诱导流模型,并根据可变翼型的构型对ONERA动态失速模型进行改进,建立了可变翼型动态失速气动模型.该模型克服了现有方法在动态失速状态下计算精度不高、未知状态量过多及计算复杂等缺点.采用该模型,计算了后缘小翼作简谐偏转运动的可变翼型在翼型无变距运动和翼型有变距运动两种情况下的气动载荷,并把计算结果与实验结果及ONERA模型计算结果比较,验证了本文建立的可变翼型动态失速气动模型的准确性.
Variable airfoils have gained more and more attention in raising lift, reducing vibration and noise, and retarding dynamic stalling, etc. However, there is still a lack of accurate and efficient aerodynamic model of variable airfoil dynamic stall. The dynamic stall-induced loop is added to the two-dimensional induced flow model, and the ONERA dynamic stall model is modified according to the variable airfoil configuration. A dynamic aerodynamic model of variable airfoil dynamic stall is established. Dynamic stall state, the calculation accuracy is not high, the unknown state quantity is too much and the computational complexity and other shortcomings.Using the model, the trailing edge winglets as simple harmonic deflection of variable airfoils in the airfoil without pitch motion and airfoil The results show that the aerodynamic loads of the dynamic aerodynamic model with variable airfoils are validated by comparing the calculated results with the experimental results and the calculation results of the ONERA model.