对装有“前端襟翼”和“前缘襟翼”的７４°后掠三角翼，在迎角０°～９０°范围的定常和非定常（俯仰振动，ｆ＝０．４，０．８，１．２Ｈｚ）的空气动力特性以及襟翼的控制作用作了实验研究。定常流的实验结果与解Ｎ－Ｓ方程的计算结果作了比较。非定常俯仰振动使气动特性的变化出现迟滞现象，但仍能保持襟翼对定常流控制所具有的优越性。不装襟翼的三角翼的部分校测结果与文献中相应数据一致，表明实验结果可信。 For 74 ° swept delta wing equipped with “front flaps” and “leading edge flaps”, the steady and unsteady (pitch vibration, f = 0.4, 0.8 , 1.2Hz) and the aerodynamic characteristics of the flaps were experimentally studied. The experimental results of steady flow are compared with the results of solving N-S equation. The unsteady pitch vibration causes hysteresis in the change of aerodynamic characteristics, but it still maintains the superiority of flaps in the control of steady flow. The part of the calibration results of the delta wing without flaps is consistent with the corresponding data in the literature, indicating that the experimental results are credible.