颤振临界速度的英文

• critical flutter speed

• "颤振"英文翻译    shimmy; tremor
• "临界速度"英文翻译    critical speed; critical vel ...
• "低于颤振临界速度的" 英文翻译 :    flutter-free
• "超临界速度" 英文翻译 :    higher critical velocity; supercritical speed; supercritical velocity
• "次临界速度" 英文翻译 :    lower critical velocity; sub-critical speed
• "高临界速度" 英文翻译 :    higher critical velocity
• "临界速度" 英文翻译 :    breakdown speed; critical speed; critical velocity; decision speed; optimum speed; speed velocity; terminal-velocity; thrashing speed; throat velocity; velocity, critical; whirling eed; whirling speed
• "亚临界速度" 英文翻译 :    subcritical speed; subcritical velocity
• "单发临界速度" 英文翻译 :    aircraft critical speed
• "埋艏临界速度" 英文翻译 :    plough-in critical speed
• "砰击临界速度" 英文翻译 :    critical slamming velocity; threshold velocity of slamming
• "转子临界速度" 英文翻译 :    critical speed of rotor
• "超流动临界速度" 英文翻译 :    critical velocity of superflow
• "低临界速度运转" 英文翻译 :    cataract
• "反横操纵临界速度" 英文翻译 :    reversal speed of wing
• "怜的超临界速度" 英文翻译 :    supercritical velocity of flow
• "临界速率, 危险速度" 英文翻译 :    critical speed
• "失速仪；临界速度指示器" 英文翻译 :    stallometer
• "临界速度，相应于转动系统共振频率的速度" 英文翻译 :    critical speed
• "超临界速率" 英文翻译 :    speed; supercritical
• "次临界速率" 英文翻译 :    speed; subcritical
• "临界速率" 英文翻译 :    critical speed
• "边界速度" 英文翻译 :    boundary velocity
• "限界速度" 英文翻译 :    limitation velocity
• "颤振速度" 英文翻译 :    flutter speed

• Both h controller and synthesis are designed when the damping uncertainties in plunge
  在稍大于颤振临界速度的风
• The numerical simulations agree well with the wind the tunnel experiments , and the critical speed is increased by 13 . 4 % . chapter 5 presents the robust flutter suppression of the airfoil
  数值仿真和风洞实验表明,这两种控制器是有效的,可将系统的颤振临界速度提高23 . 4 % 。
• Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified . and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing
  以某导弹翼面为算例，对弹翼的亚、跨、超音速的颤振临界速度进行了数值计算，部分计算结果与风洞计算结果相比较，一致性很好。
• In chapter 4 , the aeroelastic model of the whole test rig is first established by using jones ’ s approximation of theodorsen ’ s unsteady aerodynamics load . then , the numerical simulations and wind tunnel experiments for the sub - optimal flutter suppression of the airfoil model are presented
  数值仿真和风洞实验研究表明,以超声电机为控制面作动器可以有效地抑制翼段模型的颤振,颤振临界速度提高了13 . 4 % ,数值仿真和风洞实验结果基本吻合。
• Then the steady and unsteady subsonic , transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated . the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm , with baldwin - lomax turbulent model . on the basis of simulating unsteady viscous flow , coupling the structure dynamics equations , the problems of static aeroelasticity and flutter are investigated for wings and elevator
  在模拟非定常粘性绕流的基础上，与颤振运动方程相耦合，分别对机翼和全机流固耦合现象中颤振问题进行了研究，准确求解跨音速颤振临界速度，分析机翼和全机的从亚音速到超音速范围的颤振规律，并研究分析了机翼飞行迎角变化对颤振速度的影响。