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利用网格速度理论,计算机翼在锐边突风和1-cos突风下的响应,研究气动非线性和自由度耦合对翼尖加速度和升力系数的影响。采用中心格式有限体积法进行空间离散,并用双时间推进法求解非定常Euler方程。计算了刚性(沉浮)和弹性机翼在锐边突风下的加速度响应,以及刚性机翼(沉浮+俯仰)在1-cos突风下的升力响应过程,并分别与片条理论和六自由度方程的计算结果比较。在低马赫数时,各种方法得到的结果符合得很好,直接验证了网格速度方法在三维弹性和刚性机翼突风响应计算中的准确性,为计算流体力学(CFD)技术在突风响应计算中的应用打下基础。从高马赫数时CFD计算得到的结果可以看出,气动非线性对于机翼突风响应的结果影响比较大,在实际突风响应计算中必须考虑由于非线性带来的影响,而六自由度方程中各个自由度的耦合作用对升力的影响不大。
Using the theory of grid velocity, the response of the wing to the sharp-edged gust and 1-cos gust was calculated to study the influence of the coupling of aerodynamic nonlinearity and degree of freedom on the tip acceleration and lift coefficient. The finite volume method in the central format is used to discretize the space and the unsteady Euler equations are solved by the double time propulsion method. The acceleration response of the rigid wing (floating and floating) and the elastic wing under the sharp edge gust and the lift response of the rigid wing under the 1-cos gust were calculated and compared with the theory of sheet and six freedom Comparison of calculation results of degree equation. At low Mach numbers, the results obtained by the various methods are in good agreement, which directly verify the accuracy of the mesh velocity method in the calculation of the three-dimensional elastic and rigid wing gust response. For the purpose of computational fluid dynamics (CFD) Wind response calculations to lay the foundation for the application. From the results of CFD calculation at high Mach number, it can be seen that the aerodynamic nonlinearity has a great influence on the results of wing gust response. The actual gust response must consider the influence of nonlinearity, while the six degrees of freedom The coupling of each degree of freedom has little effect on the lift.