论文部分内容阅读
通过对经典Falkner-Skan-Cooke三维边界层相似解的理论分析和数值求解,结合二维边界层转捩判据的思想,采用由试验数据标定的C1准则关系式求解横流不稳定转捩位移厚度雷诺数,建立了针对固定前缘后掠角机翼的横流转捩判据,并且通过方程求解和数据拟合得到了该转捩判据的数学结果.应用该模型对30°前缘后掠角的ONERA-M6机翼和45°前缘后掠角的NLF(2)-0415无限展长机翼进行了横流不稳定转捩数值模拟.模拟结果显示:改进后的转捩模型预测所得到的转捩位置精度较高,均与后掠翼横流试验数据吻合较好,从而证明了构建的横流不稳定转捩判据的合理性和实用性.
Through the theoretical analysis and numerical solution of the classical Falkner-Skan-Cooke three-dimensional boundary layer similar to the solution, combined with the idea of two-dimensional boundary layer transition criterion, using C1 criterion formula calibrated by the test data to solve the cross-flow instability transfer displacement thickness Reynolds number, the criterion for the cross-flow rotation of a fixed-wing sweep angle wing is established and the mathematical result of the transition criterion is obtained by solving the equations and fitting the data. The numerical simulation of the cross-flow unsteady turbulence was carried out on the NLF (2) -0415 infinitely elongated wing of the ONERA-M6 wing and the 45 ° leading edge sweep. The simulation results show that the improved model of the transitional model predicts The results show that the accuracy of the transposed position is high, which is in good agreement with the data of the cross-flow test of the swept-back wing, which proves the rationality and practicability of the criterion.