The unsteady lift characteristics of a double-delta wing were studied using both experimental and numerical approaches, which were also compared with a single-delta wing with the same main wing sweep angle. It was found that by increasing the reduced frequency of pitching, the hysteresis effect of lift was magnified. Moreover, in the high reduced frequency case k = 0.48, the difference between the lift coefficients of single- and double-delta wings became rather subtle. The wing surface pressure distribution results indicated the flow phenomenon of dramatic lift losses was due to the effect of lower surface suction during the wing being pitched downstroke. It was observed that, as the reduced frequency became sufficiently high, the virtual camber effect induced by pitching could dominate the flow field, which would mitigate the impact of wing geometry on the lift characteristics.

使用实验和数值方法研究了双三角翼的非稳态升力特性，并将其与具有相同主翼后掠角的单三角翼进行了比较。发现通过增加减小的俯仰频率，升力的滞后效应被放大。此外，在高降低频率的情况下，k= 0.48时，单三角翼和双三角翼的升力系数之间的差异变得非常微妙。机翼表面压力分布结果表明，巨大的升力损失的流动现象是由于机翼向下俯仰期间较低的表面吸力的影响所致。观察到，随着降低的频率变得足够高，由俯仰引起的虚拟外倾效应可主导流场，这将减轻机翼几何形状对升力特性的影响。