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进气道性能
相关语句
  inlet performance
    Comparision of Inlet Performance with the underfuselage Inlet and Fuselage Side Inlets
    飞机机身腹部与两侧进气道性能比较试验研究
短句来源
    It analizes the effect of these parametres on the inlet performance.
    文章还分析了上述这些参数对进气道性能的影响。
短句来源
    The variation of the inlet performance parameters with the attack angles,as well as total pressure contour plots of inlet/exit at typical states,have been presented,and the relationship between flow characteristics of the inlet and its exit total pressure contour plots has also been analyzed.
    给出了在各攻角下进气道性能参数随侧滑角变化的特点及典型状态下进气道出口总压恢复系数分布图谱 ,分析了出口总压分布图谱与进气口流动之间的关系。
短句来源
    (5) The design of cowl lip is of great importance to the inlet performance at yaw, therefore, further improvement of the inlet performance will rely on the lip shapes of the cowl chosen.
    (5 )唇口的设计对进气道的侧滑角性能有着重要影响 ,进气道性能的进一步提高应考虑唇口设计的改进
短句来源
    On basis of the modeling results,the effects of Mach number,attack angle and ramp angle on the inlet performance are analyzed.
    根据此数学模型,分析了攻角和进口气流马赫数对进气道性能的影响,同时给出了斜板对进气道性能的影响。
短句来源
更多       
  inlet performance
    Comparision of Inlet Performance with the underfuselage Inlet and Fuselage Side Inlets
    飞机机身腹部与两侧进气道性能比较试验研究
短句来源
    It analizes the effect of these parametres on the inlet performance.
    文章还分析了上述这些参数对进气道性能的影响。
短句来源
    The variation of the inlet performance parameters with the attack angles,as well as total pressure contour plots of inlet/exit at typical states,have been presented,and the relationship between flow characteristics of the inlet and its exit total pressure contour plots has also been analyzed.
    给出了在各攻角下进气道性能参数随侧滑角变化的特点及典型状态下进气道出口总压恢复系数分布图谱 ,分析了出口总压分布图谱与进气口流动之间的关系。
短句来源
    (5) The design of cowl lip is of great importance to the inlet performance at yaw, therefore, further improvement of the inlet performance will rely on the lip shapes of the cowl chosen.
    (5 )唇口的设计对进气道的侧滑角性能有着重要影响 ,进气道性能的进一步提高应考虑唇口设计的改进
短句来源
    On basis of the modeling results,the effects of Mach number,attack angle and ramp angle on the inlet performance are analyzed.
    根据此数学模型,分析了攻角和进口气流马赫数对进气道性能的影响,同时给出了斜板对进气道性能的影响。
短句来源
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  “进气道性能”译为未确定词的双语例句
    EXPERIMENTAL INVESTIGATION ON PERFORMANCES OF TWO-DIMENSIONAL INLET AT SUPERSONIC SPEED
    二维超音速进气道性能实验研究
短句来源
    Mass capture ratio of forward-swept inlet is 7.7% higher than that of backward-swept inlet at Ma 4;
    当马赫数较低时,前/后掠进气道性能差别比较明显:同为50%溢流窗,来流马赫数4时,侧板前掠的进气道流量系数比侧板后掠的情形高出7.7%;
短句来源
    EFFECT OF AIRFRAME ON SUPERSONIC INLET PERFORMENCE
    机体对超音速进气道性能的影响
短句来源
    Performances estimation and optimization design of 2D mixture-compression supersonic inlet
    二元混压式超声速进气道性能预估及优化设计
短句来源
    Regression analysis on performance of a subsonic submerged inlet
    亚声速埋入式进气道性能回归分析
短句来源
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  inlet performance
For those inlet geometries veri ed by GASP, Table 3 lists some important inlet performance parameters.
      
Table 3 Inlet performance for inlet geometries obtained during the optimization procedure No.
      
Usually, such slope discontinuity is small and the results show that inlet performance bene ts from this treatment.
      
  inlet performance
For those inlet geometries veri ed by GASP, Table 3 lists some important inlet performance parameters.
      
Table 3 Inlet performance for inlet geometries obtained during the optimization procedure No.
      
Usually, such slope discontinuity is small and the results show that inlet performance bene ts from this treatment.
      


In this paper, several types of inlet are designed for a certain aircraft and the results of ground tests on their models are discussed.According to the features of the aircraft inlet (side inlet, square entrance, Large L/D and structure limitation, etc.), the paper illustrates the selecting principles of parametres in respect of entrance area, throat area, lip geometry parametre, the passage near the throat, and the area distribution in subsonic diffuser. It analizes the effect of these parametres on the inlet...

In this paper, several types of inlet are designed for a certain aircraft and the results of ground tests on their models are discussed.According to the features of the aircraft inlet (side inlet, square entrance, Large L/D and structure limitation, etc.), the paper illustrates the selecting principles of parametres in respect of entrance area, throat area, lip geometry parametre, the passage near the throat, and the area distribution in subsonic diffuser. It analizes the effect of these parametres on the inlet performance. These principles also apply to transonic or subsonic inlets.It follows from the test that the best type of these inlets is the type Ⅳ, the parametres of which are as follows. Mt= 0.75, CR=1.20, a/b= 2.84 and n = 2.25. The total pressure recovery can reach 0.908 and DCeo is equal to about -0.22 on ground state. This will not only satisfy the requirements of the Spey engine which is associated with the inlet of the aircraft, but also catch up with and surpass the level of the same types of aircraft at home and abroad.

本文针对某飞机的要求,设计了几种进气道方案,并对其地面模型的试验结果作了讨论。 文章根据某飞机进气道的特点(两侧进气,近似方形进气口,进气道长度对进气道出口直径比L/D较大以及由于总体结构的限制,使进气道形成左右、上下较大的转弯等),阐述了进气道进口面积,喉道面积,唇口几何参数,喉道附近通道部分和亚音扩压段面积分布等参数的选择原则。文章还分析了上述这些参数对进气道性能的影响。本文对进气道有关设计参数所提出的设计原则对一般的跨、亚音速进气道也是适用的。 从几种方案的试验结果得出:喉道M数为0.75,唇部收缩比为1.20,内型面的椭圆长短轴比a/b=2.84,超越椭圆指数n=2.25,内通道面积分布为第Ⅳ方案的进气道性能最好。在地面起飞状态,进气道的总压恢复系数σ可达0.908,周向总压畸变指数DC_(60)为0.22左右。该指标满足了与该机进气道配用的斯贝发动机要求,并达到和超过国内外同类机种的地面性能水平。

An external compression axisymmetric inlet model of 1/10 scale with a throat bleed slot on the surface of the centerbody was tested, at a free stream Mach number of 2.10 and at an angle of attack of 0°.Experimental results with the position of the terminal shock wave or the throttled ratio R° unchanged and various boundary layer bleed flows Wbl/Wc are presented. The results show that within the range of R* = 0.91-0.94 and flow coefficient of inlet ψ = 0.90-0.94 and with only about 1-2.5% of Wbl/Wc, the total...

An external compression axisymmetric inlet model of 1/10 scale with a throat bleed slot on the surface of the centerbody was tested, at a free stream Mach number of 2.10 and at an angle of attack of 0°.Experimental results with the position of the terminal shock wave or the throttled ratio R° unchanged and various boundary layer bleed flows Wbl/Wc are presented. The results show that within the range of R* = 0.91-0.94 and flow coefficient of inlet ψ = 0.90-0.94 and with only about 1-2.5% of Wbl/Wc, the total pressure recoveries of the inlet are raised about 4-5.8%, and the total pressure distortion DC60 is reduced by 10-54% as compared with that of the case without boundary layer bleed.Besides, at the M∞= 2.1 and a =4°, 8° angles of attack of inlet, the stability margin of the inlet may be increased about 5-10% by means of the throat boundary layer bleed.Favorable effects of the boundary layer bleed on the total pressure distortion across the channel downstream of the throat and the effects on the positions of the terminal shock wave relative to the bleed zone on the centerbody surface and on the surface static pressure distribution along the centerbody and the cowl are discussed.

本文介绍了在缩尺比为1:10的超音速飞机轴对称进气道几何喉道附近的中心锥体表面上,开了槽宽为4δ的附面层吸除缝,在自由流马赫数M_∞=2.10,迎角α=0°,以及在相同的结尾激波位置,或相同的尾塞锥位R°,不同的附面层吸除量对进气道性能的影响的初步研究结果。实验证明,在R°=0.91~0.94或流量系数φ=0.90~0.94内,用0.01的进气道捕获流量的锥面附面层吸除量,进气道的总压恢复可比无附面层吸除提高4—5.8%;周向稳态畸变降低10~54%;喘振裕度在4°~8°下,可提高5~10%。文中还特别介绍了锥面附面层吸除对几何喉道下游的通道总压分布和马赫数分布的有利影响;不同尾锥位或不同结尾激波与放气区相对位置下,附面层吸除量对锥面或外罩内表面沿程的静压恢复的影响;解释了在超临界下,中心锥肩部放气效果最差,而在稍亚临界下,波后放气效果较好的原因。

Air intake with fences installed at the entrance is investigated at low speed. With fences at a high angle of attack the steady and dynamic distortions are effectively reduced and the total pressure recovery is increased at the exit.These improvements are shown to be closely related to the reduced extent of separation along leeward wall of the intake by the fences at the angle of attack. A flow model is suggested to describe the flow in the channels formed by the fences. With this model in mind, the mechanism...

Air intake with fences installed at the entrance is investigated at low speed. With fences at a high angle of attack the steady and dynamic distortions are effectively reduced and the total pressure recovery is increased at the exit.These improvements are shown to be closely related to the reduced extent of separation along leeward wall of the intake by the fences at the angle of attack. A flow model is suggested to describe the flow in the channels formed by the fences. With this model in mind, the mechanism of the fences can be easily imagined and the performance of the slanted inlet with fences can be predicted. The effects of the position, lengths and the number of the fences on the performance of the inlet are investigated. The difference between a slanted and a pilot inlet both with fences are compared and an intake with an S-duct and fences are evaluated. Combined with less radar reflection the multi-channel inlet is shown to be attractive. The above related investigation will be helpful in intake fence design.

在低速情况下进行了进气道安装进口导流板的研究。文中用实验阐明了进气道处于大攻角下进口导流板能有效的降低其出口稳态和动态畸变,并能提高其总压恢复。文中进一步说明了进口平直段内避风侧壁面上的气流分离与出口流场的关系,提出了导流板改善气流分离的机理,并用所提出的装导流板后的流动模型进行了分析和推断。文中论述了导流板设计参数对进气道性能的影响。本文内容对设计进气道进口导流板具有参考意义。

 
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