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对后掠角分别为ｘ＝６０°、７０°和８０°尖前缘平板三角翼模型和一个前缘后掠角为（７６°＋４０°）的双三角翼模型在低速风洞中作大攻角俯仰谐波运动，振幅α＿ｍ＝３０°、６０°和９０°，缩减频率Ｋ＝０．０１～０．１２，基于根弦长雷诺数Ｒ＿ｅ＝２．７６×ｌ０￣５～８．２８×１０￣５。进行了六分量动态气动载荷测量，动态流动显示和７０°三角翼上翼面非定常压力测量，并分别与对应的静态试验结果比较。分析了运动参数包括缩减频率、振幅和Ｒ＿ｅ数、后掠角对气流动态迟滞特性的影响。
For the double-delta wing model with a sweep angle of x = 60 °, 70 ° and 80 °, and a double delta wing model with a leading edge sweep of (76 ° + 40 °) Angle pitch-harmonic motion, amplitude α_m = 30 °, 60 ° and 90 °, reduction frequency K = 0.01 ~ 0.12, based on root length Reynolds number R_e = 2.76 × l0 ~ 5 ~ 8.28 × 10 ~ 5. Six-component dynamic aerodynamic load measurement, dynamic flow display and unsteady pressure measurement on the upper wing of the 70 ° delta wing were performed and compared with the corresponding static test results respectively. The effects of motion parameters, including the reduction frequency, amplitude and R_e number, and sweep angle on the dynamic hysteresis characteristics are analyzed.