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展向吹气
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  spanwise blowing
     An investigation on the effect of spanwise blowing on unsteady aerodynamic characteristics
     展向吹气对非定常气动特性影响试验研究
短句来源
     Investigations showed that spanwise blowing is a very effective measure for controlling breakdown of leading edge vortex over the wing and improving the aerodynamic characteristics at high angle of attack.
     研究表明展向吹气是控制机翼上旋涡破裂和流动分离的一种十分有效的气动措施。
短句来源
     A summary on investigations conducted by authors,including the exploratory study of mechanism of interaction between spanwise blowing and the vortex by using flow visulization and LDV technique,investigations on various blowing configuration and factors affecting benifit due to the spanwise blowing,controlling the position of the vortex to improve drag reduction effectiveness of vortex flap and pulse spanwise blowing to save compressed air supply and improve blowing effectiveness,is presented in the paper.
     本文综述了在这一领域内的主要研究成果,包括利用流动显示和LDV技术探索展向吹气与机翼前缘涡干扰的机理,各种吹气方案和影响因素对气动特性的影响,利用展向吹气控制前缘涡位置改善涡襟翼效率的研究以及脉冲吹气提高吹气效率等方面的研究。
短句来源
  “展向吹气”译为未确定词的双语例句
     the magnitudes of lift-enhancement increase with blowing momentum coefficients when blowing,which suggests that the indirectly controlling the wing vortex,delaying its breakdown and increasing the lift with the technique of canard-spanwise blowing for close-couple canard-configurations are possible.
     当对鸭翼进行展向吹气时,吹气动量系数越大,布局的增升量也越大,说明利用鸭翼展向吹气技术达到间接控制机翼涡,延迟机翼涡的破裂,增加机翼的升力是完全可行的。
短句来源
  相似匹配句对
     An investigation on the effect of spanwise blowing on unsteady aerodynamic characteristics
     吹气对非定常气动特性影响试验研究
短句来源
     PV premiere Vision coming to China
     带着期待中国走来
短句来源
     Analysis of spanwise circulation for running wing piece
     转动翼板的环量分析
短句来源
     Investigations showed that spanwise blowing is a very effective measure for controlling breakdown of leading edge vortex over the wing and improving the aerodynamic characteristics at high angle of attack.
     研究表明吹气是控制机翼上旋涡破裂和流动分离的一种十分有效的气动措施。
短句来源
     SEMA SHOW NEW
     新品
短句来源
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  spanwise blowing
The visualization of the flowfield about a delta wing with spanwise blowing
      
This paper describes a nonintrusive method for the visualization of the flow about a delta wing with spanwise blowing jets, based on the schlieren technique.
      
The visualization of the leading-edge vortex trajectories and their breakdown, as well as the influence of the jets on them is achieved by spanwise blowing of air.
      
The visualization of the jets' paths and the effects of the leading-edge vortices on these paths is achieved by spanwise blowing of helium.
      
Also, the mass flow estimate is artificially high due to the assumption of a constant thickness slot and constant spanwise blowing.
      
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Force measurements of a whole aircraft model with a delta wing and spanwise blowing were carried out and flow visualization of its semi-span model were conducted in the FL-8 and FL-5 wind tunnels. Several techniques, such as oil flow, water fog, helium bubble, fluorescent minitu-fts, were employed in the flow visualization.The comparative test investigations of two blowing techniques, i.e. the flap spanwise blowing and the blown flap, were completed with the identical model in the same wind tunnel.It is found...

Force measurements of a whole aircraft model with a delta wing and spanwise blowing were carried out and flow visualization of its semi-span model were conducted in the FL-8 and FL-5 wind tunnels. Several techniques, such as oil flow, water fog, helium bubble, fluorescent minitu-fts, were employed in the flow visualization.The comparative test investigations of two blowing techniques, i.e. the flap spanwise blowing and the blown flap, were completed with the identical model in the same wind tunnel.It is found that the flap shoulder vortex is generated over the flap instead of the jet vortex when the spanwise blowing is applied to a flap with large deflection angles. Furthermore, the flap shoulder vortex locates always ahead of the jet. Its vorticity originates from flap shoulder separation. Axial velocity of the vortex is provided by entrainment effect of the jet. It is also shown that the lift augmentation caused by the flap span-wise blowing should not be attributed merely to the boundary layer control and is mainly due to the vortex control.Lift increments originated from the flap spanwise blowing consist of two parts: one acts on the flap, another on the wing. The lift increments which approach to those of the blown flap are obtained at a small jet momentum coefficient(about 0.012) which can be provided by recent engines through selecting optimum configurations and parameters of nozzle. Therefore, it is possible to improve landing performance of aircraft markedly. For the first time a two-branch nozzle is applied, in result the flow over the whole surface of the flap is ameliorated.

本文分析了在FL-8和FL-5风洞完成的一个三角翼飞机模型展向吹气全模测力和机翼半模流态实验中的襟翼展向吹气的气动效果,并且与同一模型在同一风洞中所得到的吹气襟翼结果进行了比较。 明确了在大偏度襟翼上展向吹气,产生的集中涡是“肩线涡”,而不是“喷气涡”。指出涡控制是襟翼展向吹气增升的重要原因,而不应单纯归结为边界层控制问题。通过对喷嘴形状和参数的优选,实现了用当前发动机实际能提供的小的吹气动量系数(约0.012)取得与吹气襟翼相近的升力增量。从而有可能显著地改善飞机的着陆性能。首次采用了“两叉喷嘴”,使整个襟翼面的流动获得改善。由于这项技术结构简单、重量轻、不占用机翼内部空间、生存力强,因此可望成为飞机设计中一种可供选用的动力增升方案。

Vortex and flow separation control has been one of the important subjects in the field of aerodynamics.Investigations showed that spanwise blowing is a very effective measure for controlling breakdown of leading edge vortex over the wing and improving the aerodynamic characteristics at high angle of attack.A summary on investigations conducted by authors,including the exploratory study of mechanism of interaction between spanwise blowing and the...

Vortex and flow separation control has been one of the important subjects in the field of aerodynamics.Investigations showed that spanwise blowing is a very effective measure for controlling breakdown of leading edge vortex over the wing and improving the aerodynamic characteristics at high angle of attack.A summary on investigations conducted by authors,including the exploratory study of mechanism of interaction between spanwise blowing and the vortex by using flow visulization and LDV technique,investigations on various blowing configuration and factors affecting benifit due to the spanwise blowing,controlling the position of the vortex to improve drag reduction effectiveness of vortex flap and pulse spanwise blowing to save compressed air supply and improve blowing effectiveness,is presented in the paper.

旋涡和流动分离的控制一直是空气动力学研究的一个重要课题。研究表明展向吹气是控制机翼上旋涡破裂和流动分离的一种十分有效的气动措施。本文综述了在这一领域内的主要研究成果,包括利用流动显示和LDV技术探索展向吹气与机翼前缘涡干扰的机理,各种吹气方案和影响因素对气动特性的影响,利用展向吹气控制前缘涡位置改善涡襟翼效率的研究以及脉冲吹气提高吹气效率等方面的研究。

A test setup for the determining of aerodynamic characteristics in pitching oscillation with spanwise blowing and relevant testing technique have been developed recently.Some experimental investigations for a 60 deg delta wing body combination to explore the effects of spanwise blowing on the hysteresis characteristics have been conducted in the China Aerodynamics and Research Development Center (CARDC) 3.2m diameter subsonic wind tunnel for the force measurements and 1.28m×0.78m low speed wind tunnel in...

A test setup for the determining of aerodynamic characteristics in pitching oscillation with spanwise blowing and relevant testing technique have been developed recently.Some experimental investigations for a 60 deg delta wing body combination to explore the effects of spanwise blowing on the hysteresis characteristics have been conducted in the China Aerodynamics and Research Development Center (CARDC) 3.2m diameter subsonic wind tunnel for the force measurements and 1.28m×0.78m low speed wind tunnel in Nanjing University of Aeronautics and Astronautics (NUAA) for the flow visualization with the reduce frequency from 0.01 to 0.078 and amplitude of 20 deg at the mean angle of attack of 20 ,30 and 40 deg,respectively. The results indicated that the spanwise blowing (SWB) over the wing could improve the vortex flow significantly and reduce the differences between the flow patterns at the same angles of attack in upstroke and downstroke,and hence improve the hysteresis of aerodynamic characteristics.

本文给出了利用展向吹气控制飞行器正弦俯仰振荡的气动力迟滞环。模型为60°三角翼翼-身组合体;俯仰振荡的减缩频率为0.039和0.078,实验迎角范围为0°~60°。实验研究包括流态显示和气动力测量。结果表明展向吹气可以明显改善飞行器动态运动中的气动力迟滞特性,使上仰和下俯过程中气动力的差异显著减小,即减小了“迟滞环”的宽度。

 
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