论文部分内容阅读
以高空长航时无人机(UAV)翼型研究为背景,对超临界RAE2822翼型在高空高亚声速下的低雷诺数气动特性进行了数值模拟及优化设计研究。采用求解雷诺平均N-S方程的有限体积法,对典型低雷诺数下RAE2822翼型绕流进行数值模拟,验证了SSTk-ω湍流模型的可靠性和准确性;基于不同高度不同雷诺数下RAE2822翼型的计算气动力对比分析,研究了高度增大所带来的低雷诺数效应;通过对低雷诺数下超临界翼型表面流场结构及流动机理的详细分析,提出了一种弱化激波的翼型设计思想,并通过优化算例验证了该思想的可行性。
Based on the UAV airfoil research at high altitudes, the numerical simulation and optimization design of the low Reynolds number aerodynamic characteristics of a supercritical RAE2822 airfoil at high altitudes and high subsonic velocities are studied. The finite volume method for solving the Reynolds-averaged Navier-Stokes equations is used to simulate the flow around RAE2822 airfoil with typical low Reynolds number. The reliability and accuracy of the SSTk-ω turbulence model are verified. Based on the RAE2822 airfoil with different Reynolds numbers, , The low Reynolds number effect caused by the height increase is studied. By analyzing the structure and flow mechanism of the supercritical airfoil at low Reynolds number, a new method to weaken the shock wave Airfoil design idea and verify the feasibility of the idea by optimizing the example.