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来流
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  inflow
    however,the difference decrease to 2.6% when the inflow Mach number increases to Ma 8.
    而当来流马赫数为8.09时,侧板前掠的进气道流量系数仅高2.6%。
短句来源
    INFLUENCE OF NON-UNIFORM INFLOW UPON THE THREE-DIMENSIONAL GAS-SOLID CYLINDER WAKE
    非均匀来流对三维气固圆柱尾迹的影响
短句来源
    The flowfields and wave system in cave on aft body also change very much with the different inflow condition and various locations of OSW.
    不同的穿越位置时 ,由于不同的来流条件 ,使物体上尾部凹坑内的流场和波系发生很大的变化。
短句来源
  incoming flow
    NUMERICAL SIMULATIONS OF FLOW-FIELDS IN AXIAL-SUPERSONIC INCOMING FLOW FAN ROTORS
    轴向超音来流风扇转子流场数值模拟
短句来源
    EFFECTS OF INCOMING FLOW ASYMMETRY ON SHOCK TRAIN STRUCTURES IN CONSTANT-AREA ISOLATORS
    隔离段进口非对称来流对激波串结构的影响(英文)
短句来源
    There are great differences between ground test of a flight vehicle's aerodynamics and that of a dual-mode scramjet When ground test facilities are used to do experiments on a dual-mode scramjet engine, the components of incoming flow and its parameters, including total pressure, total temperature (or total enthalpy) and velocity must be simulated.
    双模态冲压发动机的地面试验研究同飞行器的空气动力学地面试验研究有很大的不同。 进行双模态冲压发动机地面试验研究时,必须要求试验设备能模拟实际飞行条件下来流气体的组分、总压、总温(或总焓)以及来流气体的流动速度;
短句来源
    A wind tunnel is designed under asymmetric incoming flow and the compression fields in the isolator have been investigated using wall static and pitot pressure measurements, schlieren photography.
    本文采用试验研究、数值模拟和理论分析相结合的方法对非对称超声速来流条件下隔离段流动进行了研究,设计了针对非对称超声来流矩形隔离段流场研究的直联式试验风洞,在模拟进气道出口流场的各种非对称进口条件下进行了吹风试验。
短句来源
    The performance of the compression ramp are studied mostly at the design point and off-design point in the condition of uniform supersonic incoming flow, and slightly at the design point in the condition of non-uniform incoming flow.
    文中主要研究了压缩面在均匀来流条件下设计点与非设计点的气动性能,也简略地分析了非均匀来流条件下设计点的气动性能。
短句来源
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  “来流”译为未确定词的双语例句
    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
    Influence of Inlet Water Ingestion on Aero-Engine Fan-Compressor Performance
    来流含水对航空发动机风扇/压气机特性的影响
短句来源
    3. The effects of such elements as primary flow total pressure,flow rate,degree of fuel rich,nozzle structure,flying speed and secondary combustion on ejecting mode performance were researched.
    3.研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响,发现实验样机构型在0.7Ma以上的飞行条件下可以获得推力增强,而在0.7Ma以下无推力增强。
短句来源
    Experimental and numerical methods were conducted in study the Dual-mode Scramjet(DMS) and the subsonic combustion was translated into supersonic combustion, at the simulated condition, which corresponds the flying state of Ma=6,H=25km.
    本文采用试验和数值仿真的方法对双模态超燃冲压发动机进行了研究,实现了在模拟飞行高度25km、来流马赫数M=6的亚燃模态和超燃模态,以及亚燃模态向超燃模态的转换。
短句来源
    The flow field and plasma sheath layer properties such as shock-wave shape, surface pressure, gas components, electron density and electronic collision frequency and so on are given in the range of free stream M∞ = 20-26, Re= (ρ U ,a)/μ= 1.5 ×103 -5.5×106 (where a is the radius of blunted nose).
    在来流条件M_∞=20~26,Re_∞=(p_∞u_∞α)/μ_∞=1.5×10~3~5.5×10~6(α为头部半径)的参数范围内,给出了绕流流场和等离子体鞘层诸特性,如激波形状、电子密度和电子碰撞频率等。
短句来源
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  inflow
The microorganisms in activated carbon effluent consisted mostly of heterotrophic bacillus and the total bacteria number was five times as high as that of the inflow, i.e.
      
Nitrogen removal of wetlands under 40 different inflow loadings were studied in the field during 15 months.
      
The outflow loading and total nitrogen (TN) removal rate of these beds under different inflow loadings and pollution loadings were investigated.
      
The inflow loadings of 4 subsurface flow systems (SFS) ranged from 400 to 8000 mg·(m2·d)-1, while outflow loadings were less than 7000 mg·(m2·d)-1.
      
The results showed that the inflow and outflow loading of TN removal rate in SFS presented an obvious linear relationship.
      
更多          
  incoming flow
The nonsteady conditions in the incoming flow are characterized by the Strouhal number.
      
For a network with Poisson incoming flow of customers (particles) and unit time of the motion of servers (annihilators), we obtain the limit distribution of the number of customers at the node for a fixed general number of nodes.
      
For a network with Poisson incoming flow of customers (particles) and unit time of the motion of servers (annihilators), we obtain the limit distribution of the number of customers at the node for a fixed general number of nodes.
      
A numerical analysis reveals a nonattracting chaotic invariant set Λ that determines the scattering and trapping of particles from the incoming flow.
      
The hierarchy is found to have certain properties due to an infinite number of intersections of the stable manifold in Λ with a material line consisting of particles from the incoming flow.
      
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A numerical calculative method of computing aerodynamic characteristics for sideslipping thin wings of arbitrary planform with dihedral in subsonic flow is presented in this paper. It extends the Vortex Lattics Method used for freestream flow that is paralled to the symmetric plane of the wing to sideslip with the aid of introducing a new coordinate system.Some concrete examples given in the paper were compared with other available methods and experimental values. The results of comparision are satisfied.

本文利用变换坐标的方法,把处理来流平行于机翼对称面的涡格法推广到有侧滑的情况去.文中计算了亚音速流中侧滑薄翼的气动特性。机翼可以是任意平面形状和具有上反角。文中给出了一些算例,并把其结果与其他方法和实验数据比较,结果是令人满意的。

Experimental results of heat transfer to rough walls are given here for sphere cone models at Mach number 5. The nose radius of the models is 27.4mm and base diameter 60mm. Five models have been tested with different roughness in its bead diameter range from 0 to 0.9mm. The tests were conducted in a conventional hypersonic wind tunnel at total pressures from 10kg/cm2 and Reynolds numbers ReD from 0.8×106 to 3.6×106.The test results indicate that the smooth wall model heating is the laminar flow heating, its...

Experimental results of heat transfer to rough walls are given here for sphere cone models at Mach number 5. The nose radius of the models is 27.4mm and base diameter 60mm. Five models have been tested with different roughness in its bead diameter range from 0 to 0.9mm. The tests were conducted in a conventional hypersonic wind tunnel at total pressures from 10kg/cm2 and Reynolds numbers ReD from 0.8×106 to 3.6×106.The test results indicate that the smooth wall model heating is the laminar flow heating, its heat flux at the stagnation point is quite close to the theoretical data, and the influence of roughness at low total pressure (10kg/ cm2) occurs mainly to promote the transition and development of a boundary layer. With the increasing total pressure in the wind tunnel the static pressure on model and local Reynolds numbers increase correspondently. In this case the effect of roughness on heat transfer becomes remarkable, and the most remarkable region appears at sonic point region on the nose. At the highest total pressure (pt =45kg/cm2) and with the largest roughness (d = 0.9mm) the ratio of rough wall heat flux to laminar flow smooth one could be up to 4 except at stagnation point, where it could approach 6. Its raise seems to be related to the local shape change in the vicinity of the stagnation point.

本文介绍了来流马赫数5的条件下,典型球锥模型的粗糙壁热交换实验结果。模型头部半径R为27.4毫米,底部直径D为60毫米,对五个不同粗糙度的模型进行了实验。模型表面粗糙颗粒直径d分别为0、0.3、0.5、0.7、0.9毫米。风洞前室总压P_t为10~45公斤/厘米。,相应的来流雷诺数R_(eD)为(O.8~3.6)×10~6。 实验结果表明:光滑壁模型表面是层流加热,驻点热流与层流理论计算值较一致。粗糙度的影响,在低总压条件下(10公斤/厘米)主要在于促使边界层的转捩和发展。随着风洞总压的提高,物面静压和局部雷诺数的相应增大,粗糙度对热流的影响才明显增强,而严重的区域在端头。在实验最大粗糙度和最大总压条件下(d=O.9毫米、p_t=45公斤/厘米。),除驻点值外,热流与光滑壁层流驻点值相比(q_i/q_(so))的峰值在音点区域且接近4,而在驻点,此模型有别于其它模型,较为特殊,比热流最大值接近6,看来这可能与驻点局部外形变化有关。

An iterative method for solving two-dimensional compressible boundary layer equations and steady state equations of heat conduction simultaneously is presented, and also a FORTRAN program for calculation of the local convec-tive heat transfer coefficients over air-cooled vane surface by means of this method is provided. The approximate integral method is used for solving boun- dary layer equations end the finite element method is applied to calculating the steady temperature field of the blade.The input of the...

An iterative method for solving two-dimensional compressible boundary layer equations and steady state equations of heat conduction simultaneously is presented, and also a FORTRAN program for calculation of the local convec-tive heat transfer coefficients over air-cooled vane surface by means of this method is provided. The approximate integral method is used for solving boun- dary layer equations end the finite element method is applied to calculating the steady temperature field of the blade.The input of the program consists of geometry of the blade, pressure or velocity distribution of gas flow external to the boundary layer, entrance flow conditions, internal cooling conditions, nodal numbers and coordinates of the elements. The output includes all principal boundary layer parameters, such as heat transfer coefficients and temperature distribution on the surface, and temperature distribution inside the blade. A numerical example has been calculated and the results are favourably compared with the theoretical and experimental data given by other authors.

本文提出了联立求解二维可压缩边界层方程组和稳定导热方程的迭代法,从而修正了文献[1]假定物体表面温度等于来流总温的局限;同时提供了用这种方法计算气冷叶片表面局部对流换热系数的完整的FORTRAN程序。文中用近似积分法求解边界层方程组,用有限元素法计算叶片的稳定温度场。算例的结果与有关的理论及实验结果相接近。

 
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