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.
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.
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