A method for treating experimental data obtained on a setup with free oscillations over the pitching angle of the model and for determining the unsteady aerodynamic characteristics of the pitching moment coefficient is described. It is found that the pitching moment coefficient of a re-entry vehicle model at Mach numbers M = 2 and 2.25 and fixed angles of attack a depends non-linearly on the rate of change of the angle α. This circumstance makes the concept of aerodynamic derivatives inappropriate for mathematical description of the pitching moment coefficient.

中文翻译：

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再入飞行器模型的气动力矩和俯仰阻尼的特定特征，在超音速下具有自由振动

描述了一种方法，该方法用于处理在模型的俯仰角上具有自由振荡的设置上获得的实验数据，并确定俯仰力矩系数的非稳态气动特性。据发现，在马赫数再入车辆模型的俯仰力矩系数M = 2个2.25和固定角度攻击的一个取决于非线性的角度α的变化率。这种情况使得空气动力学导数的概念不适用于俯仰力矩系数的数学描述。