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基于当地流活塞理论推导了旋成体机身和任意外形三维机翼非定常气动力计算公式,结合CFD数值仿真,将当地流活塞理论推广用于复杂外形飞行器全机大攻角超声速颤振计算。以翼-身组合体面对称外形飞行器为例,进行带攻角的超声速颤振计算,并与非定常气动力采用CFD全数值仿真求解得到的颤振计算结果比较,验证了本文方法的正确性和效率。
Based on the local flow piston theory, the unsteady aerodynamic formula of the fuselage body and arbitrary shape three-dimensional wing is deduced. Combining with the CFD numerical simulation, the local flow piston theory is generalized for the calculation of the supersonic flutter of the complex aircraft with a large angle of attack. Taking the wing-body combination of decent symmetric profiled aircraft as an example, the calculation of supersonic flutter with angle of attack is carried out and compared with the flutter calculation results of unsteady aerodynamics obtained by CFD numerical simulation. The correctness of this method is verified. effectiveness.