论文部分内容阅读
介绍了一种控制机翼失速特性的新技术——流动偏转器。通过对二维翼型的数值模拟,研究了流动偏转器高度对控制效果的影响。采用PIV测量作为流动显示手段,验证了较低雷诺数(Re=6.32×105)时流动偏转器对机翼流动分离的控制效果。基于数值模拟结果和正交设计方法,对流动偏转器在更高雷诺数(Re=1.76×106)下进行了风洞测力实验研究。研究结果表明,流动偏转器可以有效控制机翼失速特性,能够抑制机翼大攻角下的流动分离,推迟失速攻角和增加升力。对测力实验结果的正交分析还给出了以16°到30°攻角范围内平均气动力最佳为目标的最优水平组合。
A new technique to control the stall characteristics of the wing, the flow deflector, is introduced. Through the numerical simulation of two-dimensional airfoil, the effect of flow deflector height on the control effect is studied. The PIV measurement was used as a flow indicator to verify the control effect of the flow deflector on the wing flow separation at a low Reynolds number (Re = 6.32 × 105). Based on the numerical simulation results and the orthogonal design method, a wind tunnel test on the flow deflector under a higher Reynolds number (Re = 1.76 × 106) was carried out. The results show that the flow deflector can effectively control the stall characteristics of the wing, and can suppress the flow separation at a high angle of attack, delay the stalling attack angle and increase the lift. Orthogonal analysis of the results of the force measurement experiment also gives the optimal level combination aiming at the best average aerodynamic force in the range of 16 ° to 30 ° angle of attack.