The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
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.
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 estimation procedure is shown by using an example and the estimation results of variation of longitudinal aerodynamic derivatives with Angle of attack are obtained.
用一算例说明了估计过程，获得了纵向气动导数随迎角变化的估计结果。
The aerodynamic drag of different models at zero angle of attack in the experiment is calculated using the simplified procedure.
在零攻角实验时不同模型的空气动力阻力是采用简化方法来计算的；
The methods are devoted to determining aerodynamic performances for asymmetrical body with Angle of attack, Angle of side slip and roll Angle.
可用来计算有攻角、侧滑角、滚转角的非对称体的气动特性。
When flapping-wing flight at small attack Angle, wing had wing-blade improve effectively aerodynamic characteristic of flapping-wing.
当扑翼在小迎角飞行时，机翼带翼刀可以有效地改善扑翼的气动特性。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。
The results showed the influence of pivoting-stator on the turbine's aerodynamic performance was combined effect of cascade convergence, attack Angle and out-flow Angle.
研究表明，可调导叶对涡轮性能的影响是叶栅收敛度、气流冲角与出气角的综合影响。
The aerodynamic characteristics of the free wing are investigated in this paper. The wind tunnel test results shows that the control of the angle of attack of the fre…
通过风洞试验，对带升降副翼控制的自由翼气动特性也进行了实验研究，验证了位于自由翼后缘的升降副翼可有效地控制自由翼相对气流的平衡迎角。
The aerodynamic characteristics of the free wing are investigated in this paper. The wind tunnel test results shows that the control of the angle of attack of the fre…
通过风洞试验，对带升降副翼控制的自由翼气动特性也进行了实验研究，验证了位于自由翼后缘的升降副翼可有效地控制自由翼相对气流的平衡迎角。
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