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    FURTHER RESULTS OF THE BOUNDARY ELEMENT METHOD FOR PLATE BENDING
    平板弯曲问题边界元法的进一步结果
    Turbulence Model of Water Jet with Polymer Additives and its Numerical Results
    高聚物稀溶液射流的湍流模型及其数值结果
    Numerical Modeling of Kelvin-Helmholtz Instability and Rayleigh-Taylor Instability at Large Deformation Stage (Ⅰ) Numerical Methods and the Numerical Results of Rayleigh-Taylor Instability
    Kelvin-Helmholtz不稳定性和Rayleigh-Taylor不稳定性大变形发展阶段的数值模拟——(Ⅰ)数值方法和Rayleigh-Taylor不稳定性的数值模拟结果
    COMPARISON BETWEEN THE NONEQUILIBRIUM STATISTICAL MODEL Of CRITICAL COMBUSTION-EXPLOSION OF COMBUSTIBLE GAS AND EXPERIMENTAL RESULTS
    可燃性气体临界燃烧爆炸的非平衡统计模型与实验结果比较
    THE ANALYSIS OF MONITORING RESULTS OF DYNAMIC RESPONSE FOR W 11 4 PLATFORM STRUCTURE
    涠11-4平台结构动态响应监测结果分析(涠11-4平台原位监测研究之二)
    The Sidewall Boundary Layer Control for Larger 2 D Low Speed Wind Tunnel and Its Effect on Airfoil Experiment Results
    大型低速二元风洞侧壁边界层控制及对单段翼型实验结果的影响
    The results are of practical significance in the application of Lamb waves for nondestructive evaluation of material damage.
    所得结果对应用超声兰姆波评价板材疲劳损伤具有实际意义。
    Then, TS-SEP is evaluated and verified by using two advanced nickel-base superalloys, Rene95 at 650℃and AF2-1DA at 760℃. The results indicate that TS-SEP can predict the creep-fatigue life of Rene95 at 650℃and AF2-1DA at 760℃more reliable than SEP.
    通过Rene95和AF2-1DA两种镍基高温合金蠕变疲劳试验数据的初步验证,结果表明:TS-SEP比SEP具有更可靠的预测结果,对Rene95材料基本试验的预测精度有97.5%在2倍因子范围内,对AF2-1DA材料基本试验的预测结果全在2倍因子范围之内。
    The results show that both surface defects and their shoulders significantly accelerate the fatigue damage with the 10Cr4Ni4Mo4V steel having better fatigue resistance than Cr4Mo4V.
    结果表明,表面缺陷以及缺陷边缘的突起均使材料疲劳性能劣化,10Cr4Ni4Mo4V的接触疲劳性能优于Cr4Mo4V。
    The results of simulation reveal that in the tensile process there are three of all four {111} family planes to be activated to glide,dislocations are nucleated in the region near the void surface and then move outside on three {111} family planes as the void grows.
    模拟结果表明,在沿〈111〉晶向冲击加载后,在面心立方(fcc)结构中的4族{111}晶面中有3族发生了滑移。
    The results indicate that the pressure profiles show two dimensional structure and the detonation wave propagation transfers from axial direction to radius direction.
    结果表明,大板实验中TATB基炸药爆轰波传播过程中的压力剖面具有“二维结构”,且爆轰波传播方向由轴线方向逐渐向半径方向转变。
    The measurement results show that the absolute average of relative deviations is 0.65%.
    结果显示,该测量系统的相对偏差绝对平均值为0.65%,验证了该方法原理的正确性及测量系统的准确性。
    In order to analyze the validity of testing results for CCCD-SHPB dynamic fracture test system,3-D dynamic finite element method was employed to investigate the effects of specimen's geometric size and incident/transmitted bar's material on the testing results.
    为了分析CCCD-SHPB动态断裂试验系统试验结果的有效性,采用3维动态有限元方法分析了试件几何尺寸和入射杆、透射杆材料对实验结果的影响。
    All the results further verify the adaptability of the GAO-YONG turbulence model, without using empirical coefficients and wall functions, to real turbulent flow with pressure gradient.
    通过与实验结果以及BL模型计算结果的比较,表明不需要任何经验系数及壁面函数的GAO-YONG不可压湍流模型方程组能够对有压力梯度的湍流流动做出更好的预测。
    It put forward the method to determine plastoelastic fatigue notch factor by means of experimental results contrasting smooth specimen with notch specimen.
    借助于光滑试件和缺口件的对比实验结果,提出确定弹塑性疲劳缺口系数的方法。
    Results of the numerical simulation show that this method is adequate for the damage evaluation of tower truss structures.
    数值模拟结果表明,本文方法适用于塔架类结构的损伤评估。
    The results show that in Mode Ⅰ tests, 40Cr steel specimens failed by cleavage fracture, while 30CrMnSiNi2A steel specimens failed to a large extent by ductile fracture.
    结果表明,Ⅰ型实验中40Cr钢为解理型断裂,而30CrMnSiNi2A钢则在较大程度上表现出延性断裂的特征;
    With Duffy's shear modulus of molybdenum, the results of Y/G is obtained. Between 10.0 GPa and 16.0 GPa, Y/G is near to 0.02, but departure above 16.0 GPa. It is more reasonable to think Y/G consistent a linear relationship Y/G=0.0007+0.0001P.
    根据Duffy等人剪切模量的结果,发现Mo的Y/G在10.0GPa-16.0GPa之间接近于0.02,而在其他压力范围均偏离该值,在整个实验压力范围内Y/G似乎更加接近Y/G=0.007+0.001P的线性关系。
    The velocity measurement results of the flyers with two different sizes of φ0.7mm×0.025mm and φ0.5mm×0.025mm are given.
    给出了两种尺寸φ0.7mm×0.025mm和φ0.5mm×0.025mm飞片的速度测试结果
    Some Exact Results Concerning Thermoelastic Properties of Hollow Sphere Composites
    空心球复合材料热弹性性质的一些精确结果
 

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