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冲击射流噪声
相关语句
  impinging jet noise
     A kind of shield method for reducing supersonic gas impinging jet noise
     一种超声速气体冲击射流噪声的屏蔽抑制方法
短句来源
     ON THE SAW-TOOTH CHARACTERISTIC AND ITS MECHANISM OF THE IMPINGING JET NOISE FROM SMALL DIAMETER NOZZLE ONTO LARGE FLAT PLATE
     小口径喷嘴冲击射流噪声锯齿特性及机理研究
短句来源
  “冲击射流噪声”译为未确定词的双语例句
     Experimental investigation on noise characteristics of jets impinging on concave and convex plates
     凹凸板冲击射流噪声特性的实验研究
短句来源
  相似匹配句对
     On the Characteristics and Mechanism of the Discrete Frequency Noises of Impinging Jet
     冲击射流离散频率噪声的特性及机理
短句来源
     Experimental investigation on noise characteristics of jets impinging on concave and convex plates
     凹凸板冲击射流噪声特性的实验研究
短句来源
     SHOCK ASSOCIATED NOISE FROM CHOKED JETS
     阻塞喷注的冲击噪声
短句来源
     ON IMPINGING JET RESEARCH
     冲击射流的研究概述
短句来源
     A Kind of Shield Method Used to Suppress Supersonic Impinging Jet Discrete Frequency Noise
     超音速冲击射流离散频率噪声的屏蔽抑制方法
短句来源
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  noise directivity
Another issue to be addressed is the fan noise directivity.
      
The combustion noise directivity pattern obtained from four turbofan engines shows only minor directivity effects.
      


To investigate the noise characteristics of the impinging jet from a small nozzle, measurement of far field sound pressure level was performed for the aerodynamic noise generated by subsonic and supersonic jet from a 3mm-diameter axisymmetric convergent nozzle normally or obliquely impacting on a large rigid flat plate. The noise directivity pattern was found to be quadrupolelike. It was also found that the total noise intensity was enhanced as the nozzle-to-plate distance increased, and its distribution had...

To investigate the noise characteristics of the impinging jet from a small nozzle, measurement of far field sound pressure level was performed for the aerodynamic noise generated by subsonic and supersonic jet from a 3mm-diameter axisymmetric convergent nozzle normally or obliquely impacting on a large rigid flat plate. The noise directivity pattern was found to be quadrupolelike. It was also found that the total noise intensity was enhanced as the nozzle-to-plate distance increased, and its distribution had a saw-teeth behaviour within the distance less than 20 nozzle-diameters.

为研究小口径喷嘴冲击射流的噪声特性 ,测量了 3 mm口径的轴对称收缩喷嘴在各种压比情况下产生的亚音速和超音速射流冲击坚固大平板产生的噪声 .发现噪声在空间呈近似四瓣分布 ,当喷嘴与平板距离减小时 ,噪声指向壁射流下游的瓣得到增强 ,反之 ,噪声指向喷嘴上游的瓣得到增强 .噪声随喷嘴距平板距离的增加呈增强的趋势 ,在距平板一定距离内有锯齿现象 .噪声随喷嘴压比的增加而增强 ,相应于各种工况 ,存在一不同的压比值 ,此压比之前 ,噪声随压比的增大而迅速提高 ,但有起伏现象 ,在此压比之后 ,噪声平缓地随压比的增大而增强

The noise of impinging jets plays an important role in designs to reduce sonic fatigue in short take-off and vertical landing (STOVL) aircraft. Far-field noise characteristics of impinging jets on concave, convex, and plane plates were analyzed using fast Fourier transform. The results show that the impinging tone dominates the discrete frequency noise with short impinging distances. The frequency of the strongest impinging tone changes in discrete steps as the nozzle pressure ratio (NPR) increases. Far-field...

The noise of impinging jets plays an important role in designs to reduce sonic fatigue in short take-off and vertical landing (STOVL) aircraft. Far-field noise characteristics of impinging jets on concave, convex, and plane plates were analyzed using fast Fourier transform. The results show that the impinging tone dominates the discrete frequency noise with short impinging distances. The frequency of the strongest impinging tone changes in discrete steps as the nozzle pressure ratio (NPR) increases. Far-field acoustic measurements indicate that the overall sound pressure levels (OASPL) logarithmically increase with the NPR which means that this increase is relatively insensitive to variations in the NPR for NPR larger than 2.5. For a jet impinging onto a concave plate, the OASPL of the far-field noise is quite sensitive to position variations of the nozzle.

冲击射流噪声研究可为减轻垂直起降型飞机的声致疲劳提供思路。用快速Fourier变换得到了不同形状冲击面条件下冲击射流的远场噪声,并分析了噪声频谱。结果表明:对于凹、凸、平三种形状的冲击面,当冲击距离较小时,冲击单音主导了离散频率噪声;冲击单音最强音的频率随压比增大呈现频级阶越的现象;射流噪声总声压级随压比成类似对数增长的关系,当喷嘴压比大于2.5后,总声压级随压比的增长趋于缓慢;对于冲击面为凹面的冲击射流,远场噪声总声压级对喷嘴位置改变非常敏感。

Taking the impact jet flow field of individual rocket as research object,this paper calculates the jet flow field near the back of the launching tube by using the numerical simulation method.The simulation results about the developing process of the jet noise flow field in the earlier working stage of the rocket motor are given.The analysis on computed results show that the initial impact wave produced by the compressed jet does severe damage to the local launching environment.This influencing factor must be...

Taking the impact jet flow field of individual rocket as research object,this paper calculates the jet flow field near the back of the launching tube by using the numerical simulation method.The simulation results about the developing process of the jet noise flow field in the earlier working stage of the rocket motor are given.The analysis on computed results show that the initial impact wave produced by the compressed jet does severe damage to the local launching environment.This influencing factor must be taken into account when designing the individual rocket to adopt a suitable structure scheme.

该文以单兵火箭冲击射流流场为研究对象,采用数值模拟技术,对定向器管尾附近区域的燃气流场进行了数值计算,给出了发动机工作早期阶段冲击射流噪声场形成过程的计算结果。通过对计算结果的分析可知:对于开放式定向器尾管结构,燃气射流压缩空气产生的冲击波会对局部发射环境造成较为严重的破坏,在进行单兵火箭结构设计时应充分考虑这一影响因素,采用合理的设计结构以避免这一现象发生。

 
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