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在某飞机模型大振幅风洞试验的基础上,分析讨论了单自由度叠加模型、动导数模型、混合模型和非定常模型的适用性。结果表明,单自由度叠加模型、动导数模型和混合模型在小攻角时均是可用的,在大攻角时都不能正确反映飞机的非定常迟滞特性;但与前两种模型相比,混合模型在中等攻角时仍然适用。对于非定常模型,无论在小攻角还是大攻角时,均能较好地反映耦合运动的非定常气动特性。
Based on the large-amplitude wind tunnel test of an airplane model, the applicability of single degree of freedom superposition model, dynamic derivative model, mixed model and unsteady model are analyzed and discussed. The results show that the single-degree-of-freedom superposition model, the dynamic derivative model and the hybrid model are all available at small angles of attack, which can not correctly reflect the non-stationary hysteresis characteristics at large angles of attack. However, compared with the former two models, The hybrid model still works at medium angles of attack. For the unsteady model, the unsteady aerodynamic characteristics of the coupled motion can be well reflected at both small attack angles and large attack angles.