计算证明在非均匀流场中俯仰力矩曲线可能发生畸变。
The calculation has provided that in the nonuniform flow field the curve of pitching moment may be distorted.
由此计算出飞行器的法向力、轴向力和俯仰力矩系数，计算结果与实验数据相符。
The aerodynamic coefficients such as the normal force, axial force, and the pitching moment of the ve-hide computed by the local method are in good agreement with the experimental data.
本文用微分方程定性理论来分析俯仰力矩曲线随迎角变化的“勺形”对飞机飞行稳定性的影响。
The theory of stability of differential equations is used to analyse the 'effect of reversal slope of pitch moment to the stability of aircraft.
介绍了差分流量调节的计算方法和内喷管与塞锥推力矢量变化的分析过程，计算产生的俯仰力矩。
The computing method of differential throttling and the analytical process of thrust vector of inner nozzle and plug were introduced. The generated moments of pitch were given.
考虑了不同飞行攻角、不同燃料流率下气动参数，包括升力系数、阻力系数和俯仰力矩系数的变化规律。
The change rules of aerodynamic parameters including lift coefficient, drag coefficient and pitch moment coefficient have been analyzed when Angle of attack and fuel flow rate is changed.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
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