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   后缘喷流 的翻译结果: 查询用时:0.322秒
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后缘喷流
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  trailing edge jets
     In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.
     另外 ,后缘喷流可以减弱乃至消除前缘涡混掺现象的发生 ,进而有利于飞行器的操纵 .
短句来源
  trailing edge jet
     Numerical Investigation of Trailing Edge Jet Effects on Flows Around Delta Wing Using Navier-Stokes Equations
     后缘喷流对三角翼绕流影响的N-S方程数值分析
短句来源
     Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation.
     本文用拟压缩性方法求解不可压流雷诺平均拟压缩N S方程组 ,对带有后缘喷流的三角翼粘性绕流进行了数值模拟 ,求解中采用了Beam -Warming隐式近似因子分解格式以及MML代数湍流模型。
短句来源
  相似匹配句对
     Numerical Investigation of Trailing Edge Jet Effects on Flows Around Delta Wing Using Navier-Stokes Equations
     后缘喷流对三角翼绕流影响的N-S方程数值分析
短句来源
     THERMAL JET OF BLACK HOLE
     黑洞的高温喷流
短句来源
     It is exhalation sedimentation products.
     是喷流沉积产物。
短句来源
     ④Osteophyte formation of the vertebrae.
     4 )椎体后缘骨赘 ;
短句来源
     In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.
     另外 ,后缘喷流可以减弱乃至消除前缘涡混掺现象的发生 ,进而有利于飞行器的操纵 .
短句来源
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  trailing edge jet
Effects of a vectored trailing edge jet on delta wing vortex breakdown
      
Flow visualization was used to study the effects of a vectored trailing edge jet on the leading edge vortex breakdown of a 65° delta wing.
      


Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation. The computed results indicate that the trailing edge jet has an effect to decrease the pressure and increase the axial velocity of the vortex core. So it has the effect...

Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation. The computed results indicate that the trailing edge jet has an effect to decrease the pressure and increase the axial velocity of the vortex core. So it has the effect to stabilize the vortex flow and consequently it decreases the upper wing surface pressure and increases the lower wing surface pressure, hence to increase the lift of the wing. The results further indicate that when the area of the trailing edge jet exit hole is increased, or the jet is deflected downward, the above mentioned effects become stronger.

本文用拟压缩性方法求解不可压流雷诺平均拟压缩N S方程组 ,对带有后缘喷流的三角翼粘性绕流进行了数值模拟 ,求解中采用了Beam -Warming隐式近似因子分解格式以及MML代数湍流模型。计算结果说明 ,后缘喷流使涡核压强降低 ,使涡核速度增大 ,从而对三角翼前缘分离涡有稳定作用 ,并能增大上翼面的负压值和下翼面的正压值 ,从而可以增加部分升力。计算结果还说明 ,喷口面积加大或喷流下偏会使上述作用增强

The flow visualization techniques has been used to investigate the effects of trailing edge jets on the leading edge vortex breakdown and its control of flow over a 76°/40° double Delta wing. The experimental results indicate that the trailing edge jets can delay the leading edge vortex breakdown efficiently, and this delay increases with the angle of attack. The trailing edge jets can greatly improve the asymmetrical characteristics of the leading edge vortex breakdown at large angle of attack, and the...

The flow visualization techniques has been used to investigate the effects of trailing edge jets on the leading edge vortex breakdown and its control of flow over a 76°/40° double Delta wing. The experimental results indicate that the trailing edge jets can delay the leading edge vortex breakdown efficiently, and this delay increases with the angle of attack. The trailing edge jets can greatly improve the asymmetrical characteristics of the leading edge vortex breakdown at large angle of attack, and the possible occurrence of “rock” phenomenon may be overcome. In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.

流动显示结果表明 ,喷流能有效地推迟双三角翼前缘涡的破裂 ,且随着攻角的增大 ,前缘涡破裂位置逐渐推后 ,喷流极大地改善了大攻角情况下前缘涡的非对称破裂特性 ,能有效地克服可能出现的机翼的“摇滚”现象 .另外 ,后缘喷流可以减弱乃至消除前缘涡混掺现象的发生 ,进而有利于飞行器的操纵 .

 
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