icing accretion造句

• Effect of ice accretion on aircraft flight performance
  积冰对飞机飞行性能的影响
• Computation of glaze ice accretion on airfoil
  考虑传质传热效应的翼型积冰计算
• Numerical simulation of ice accretion on airfoils
  飞机机翼结冰过程的数值模拟
• Numerical simulation of glaze ice accretion process
  瘤状冰结冰过程的数值模拟
• Numerically simulating of ice accretion on airfoil
  翼型积冰的数值模拟
• Numerical simulation of rime ice accretion process on airfoil
  飞机机翼表面霜状冰结冰过程的数值模拟
• A better numerical simulation of ice accretion on airfoil
  低雷诺数涡轮叶栅损失的实验与数值模拟研究
• 6 - group indicator for ice accretion
  6 -积冰组指示码
• The two ice accretion models corresponding rime and glaze are established
  建立了对应于霜冰和光冰的两种冰增长模型。
• Prediction of rime ice accretion and resulting effect on airfoil performance
  霜状结冰及其对机翼气动特性影响的数值模拟
• Rate of ice accretion
  -积冰速率
• Type of ice accretion
  -积冰种类
• Analysis methods and its development about effect of ice accretion on aircraft flight dynamics characteristics
  结冰对飞机动力学特性影响的分析方法及其进展
• The ice accretion is considered a quasi - steady process in which the accretion is calculated layer by layer , assuming a constant flow field during the accretion of each new ice layer
  在对结冰进行数值模拟时，结冰被当成一个准定常过程，即把冰看成是一层一层增长的，假定每一层内冰增长时流场是定常的。
• In order to investigate the effect of ice on the aerodynamic characteristics of the airfoil , ice accretion on the leading edge of the naca0012 airfoil is predicted using computational fluid dynamics in this paper
  为了研究结冰对翼型气动性能的影响，本文采用cfd的方法对naca0012翼型前缘的结冰进行预测。
• Firstly , the study about flight icing is reviewed at the beginning . the condition of icing accretion , the style of icing accretion , the parameters of icing accretion in flight , and the influence of icing accretion on the aerodynamic characteristics of an airplane are analyzed
  首先,回顾了国内外在飞机结冰方面的研究情况,对飞机在飞行中的结冰条件、结冰类型、结冰参数以及结冰对气动特性的影响进行了分析讨论。
• The three basic steps are as follows : firstly , the flow field is computed . secondly , the droplet trajectory equation is solved in order to determinate the limiting droplet trajectories and local collection coefficient . thirdly , a new iced shape is defined according to ice accretion model
  其基本步骤一般分三步：计算物体的绕流流场；求解水滴轨迹方程以确定极限水滴轨迹和收集系数；根据冰增长模型来确定新的结冰翼型形状。
• Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft , and the aircraft flight envelope change of iced and un - iced situation was computed , and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it , and the longitudinal and lateral stability and the elevator , aileron and rudder step response were also studied and simulated
  根据这些参数计算了飞机结冰后阻力系数以及典型气动导数的变化，并计算了结冰前后飞机的飞行包线；同时对结冰前后飞机的纵向、横侧动稳定性以及升降舵、副翼和方向舵阶跃操纵响应进行仿真计算。