To investigate the rolling control characteristics of canard-controlled missile with fixed-tail, a numerical simulation method based on N-S formulation was conducted.
采用以N-S方程为主控方程的数值模拟方法，进行固定尾翼鸭式气动布局导弹的气动特性和流场数值模拟。
The effect on circumgyration of carbon grain and the ablation of nose-tip during re-entry of stratagem missile is analyzed according to thermal transfer theory, thermo-aerodynamics and N-S equation.
根据气动热力学、传热传质学、N - S方程，分析了战略导弹再入时端头帽烧蚀与碳颗粒的旋转效应，研究结果表明碳颗粒的旋转有利于防热。
The effect on circumgyration of carbon grain and the ablation of nose-tip during re-entry of stratagem missile is analyzed according to thermal transfer theory, thermo-aerodynamics and N-S equation.
根据气动热力学、传热传质学、N - S方程，分析了战略导弹再入时端头帽烧蚀与碳颗粒的旋转效应，研究结果表明碳颗粒的旋转有利于防热。
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