In order to study the influence of transition on the aerodynamics of a supercritical wing,both free transition and fixed transition conditions were simulated on the basis of the threedimensional Reynolds-averaged Navier-Stokes(RANS) solver with a transition prediction method based on the eN-Database.The calculated results are consistent with the experiment data,which indicate that the numerical methods are reliable and feasible.According to the numerical results,the shock wave moves forward along the upper surface of the wing followed by forward moving transition point at the constant angle of attack(AOA),leading to an decrease in lift coefficient due to the reduced area of supersonic flow.The pressure distribution with free transition of the wing section changes from a flat to a peaky type at AOA between 1 and 1 degree at Ma =0.8.This change causes the transition point moves forward rapidly,and the approximate linear relation between the lift and the AOA is lost.%基于雷诺平均Navier-Stokes(RANS)方程耦合eN-Database转捩预测方法,对某超临界机翼风洞试验条件下自由转捩和固定转捩流动特性进行数值模拟,研究转捩对其气动性能的影响.计算结果和试验结果对比验证了本文计算方法的可靠性.计算表明:相同迎角下,机翼转捩位置前移,激波位置随之前移,超声速面积减小,机翼升力系数因而减小;Ma =0.8自由转捩时,在迎角0°～1°之间,机翼剖面上翼面压力分布由较为平坦变为尖峰型,造成转捩位置急剧前移,是小迎角升力线丧失线性的主要原因.
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