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base drag
相关语句
  底阻
     The base drag increases rapidly with increasing contraction rati o (ηA≥0.5).
     收缩比ηA较大时(如ηA≥0.5),会产生很大的底阻;
短句来源
     In this paper, the wind tunnel anti-drag tests of base drag for pyrotechnic basebleed charge including Sr(NO_3)_2-Mg-308A resin were carried out under the condition of Machnumber M=1.317 or 2.518. The analogue tests of its anti-drag effect of dynamic flight weredone on the 14.5mm bullet.
     对Sr(NO_3)_2-Mg—308A树脂烟火型底排剂,在马赫数M=1.317和2.518的条件下,进行了风洞底阻减阻试验;
短句来源
     Range of Mach numbers under test being 0.6-0.98, the experiments show that solid fuel base bleeding may eliminate base drag at Mach number in the range of 0.6-0.8, and that the base bleed technique can be used in subsonic and trasonic speeds.
     实验M数范围从0.6~0.98。 实验表明:在M=0.6~0.8范围内,药剂底排可以完全消除底阻
短句来源
     On the basis of the Interior Ballistic calculation of base bleed projectile and a great deal of firing data,this paper draws up the empiric formula of the rate of reducing base drag by the way of the multinomial regression analysis to serve as the basis of designing the same diameter complex assisted projectile.
     以某底部排气弹大量实弹射击数据和解算其底排内弹道的基础上,用多项式最小二乘法的经验回归方法拟合出该弹底阻减小率经验公式,作为研究设计同口径复合增程弹的基础。
短句来源
     Test results indicate that the standard deviations of comparison test results are generally larger than that of repeat test results in the same test conditions and the discrepancy of base drag coefficients between different wind tunnels is significantly bigger than the relevant test precision in same wind tunnels.
     实验结果表明,相同状态下对比实验结果的标准偏差普遍大于重复性实验的标准偏差,其中底阻系数测值的标准偏差明显大于同一座风洞中底阻系数的试验精度。
短句来源
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  底部阻力
     The wind tunnel tests with Ma=1.79,and the Re=1.5×10~6 based on the maximal diameter of the body indicat that the scrobiculate ringed surface can reduce the base drag evidently,but it increases the viscous forebody drag including the skin friction drag and shock wave drag.
     马赫数为1.79、基于旋成体最大直径的雷诺数为1.5×106的风洞试验表明:凹环表面可显著减小旋成体的底部阻力,但却增大了包含摩擦阻力和激波阻力的粘性前部阻力。
短句来源
     It is shown that aerospike nozzle performance losses caused by free stream primarily result from increase of lift body base drag and decrease of plug pressure distribution.
     结果表明,外流造成的性能损失主要体现在运载器底部阻力增加和塞锥表面压强降低两方面.
短句来源
     The numerical simulation with SST k-ω turbulence model shows that the scrobiculate ringed surface reduces the viscous drag by 22.4% due to the vortex cushioning effect and driving effect produced by the low speed rotating flows formed in the rings. The scrobiculate rings also weaken the pumping action of the external flow on the base dead water region behind the body of revolution,and accordingly the base drag is reduced.
     利用SSTk-ω湍流模型对试验优选模型进行了数值模拟,结果表明:凹环内部低速旋转气流产生的涡垫效应和推动效应致使旋成体的摩擦阻力减小了22.4%,凹环还能减弱外部气流对旋成体截尾底部死水区的抽吸作用,显著降低了底部阻力
短句来源
     This paper introduces a supersonic complex combination of having both beside punch engines and the influance of it's end jet flow on the tail drag and base drag of main body. According to jet flow structure mechanism and effect, four difference afterbody have been designed.
     本文介绍了具有两侧冲压发动机的超音速复杂组合体的尾喷流对主弹体尾部阻力与底部阻力的影响,并根据喷流的结构、机理与效应,设计了四种不同的后体。
短句来源
     The effects of the scrobiculate rings arranged on the rearward of bodies of revolution on the base drag,skin friction drag and shock wave drag were investigated through wind tunnel tests and numerical simulation.
     通过风洞试验及数值模拟分析了置于旋成体后部的凹环表面结构对其底部阻力、摩擦阻力及激波阻力的影响。
短句来源
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  “base drag”译为未确定词的双语例句
     The Mach numbers are 0.71~1.55.From results o f it,the base drag reduction rate with base bleed cold air is low,but it with ba se bleed burning H2+air is much higher than base bleed cold air, that its maxi mum of base drag reduction rate is 40%~120%.
     从研究结果看出,底排冷空气的减阻率确实很低,但氢加空气燃烧的底排减阻率是很高的,其最大减阻率ΔCDB max=40%~120%,比冷排气要高—个量级。
短句来源
     Analysis of Base Drag Reduced by Side Holes in the Projectile with Base Cavity
     底凹弹侧壁斜孔减小底阻分析
短句来源
     Study of the Formulation of Pyrotechnic Base-bleeding Agent for Base Drag Reduction and Range-extending of Projectiles
     烟火型排气剂的配方及减阻增程研究
短句来源
     Numerical Analysis of Complex Two-phase Flow by Base Drag Reduction Performance about Base Bleed Projectile
     复杂两相流动对底部排气弹底部减阻性能影响的数值分析
短句来源
     Then, the base bleed method is introduced on a general supersonic missile to decrease the base drag of the inlet cowl for the first time and is validated by wind tunnel test.
     本文首次将底部排气法应用于导弹上 ,结合一种具有常规气动布局的超声速导弹进行了底部排气方案设计 ,采用一种“底窝器”来提高进气道整流罩的底部压强 ,并进行了风洞实验验证。
短句来源
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  base drag
Finally, base drag is neglected, while the skin-friction coefficient is assumed to be a constant, average value.
      
The total drag is made up of pressure drag, base drag, and skin-friction drag.
      
Base drag effects on maximum lift-to-drag ratio airfoils at moderate supersonic speeds
      
The rise in base pressure or reduction in base drag has been clearly predicted for various mass injection rates and comparison with experimental data shows generally good agreement.
      
The capability to compute the base flow with base bleed at supersonic speeds has been developed and used to show the effect of mass injection on the base pressure or base drag.
      
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The paper makes an analysis of the results of wind Tunnel tests on the ball model with hollow base. It is apparent obviolls that the ball with bollow base with holes around its side wall has a favourable effect on the characteristic of drags. The results of the base drag is especially apparent in our NH-1 wind tunnel. The optimum porosity ratio is about 35%. This method will be expected to have similar satisfactory result, if it is extended to a second age ball with hollow base.

本文给出了底凹弹丸模型风洞实验结果的分析。从中可见,绕尾部带有导气孔的底凹弹丸具有令人满意的阻力特性,在NH-1风洞试验中,底部阻力的影响特別明显.最佳开孔比约为35%。若把此方法推广到第二代底凹弹丸中,将同样有效。

This paper introduces a supersonic complex combination of having both beside punch engines and the influance of it's end jet flow on the tail drag and base drag of main body. According to jet flow structure mechanism and effect, four difference afterbody have been designed. Experiment investigation shows: The main body zero drag can be reduced by faovurable interference of jet flow. Then an optimuns afterbody configuration can be obtained.

本文介绍了具有两侧冲压发动机的超音速复杂组合体的尾喷流对主弹体尾部阻力与底部阻力的影响,并根据喷流的结构、机理与效应,设计了四种不同的后体。实验研究表明,利用喷流的有益干扰,可使主弹体零阻显著下降,从而得到一种优化的后体外形。

A supersonic zero-lift drag computer program for complex missile- like body shapes has been developed. A mixed method has been developed for wave drag predicting. At first, the supersonic Area-Rule concept is used to predict the drag of complete configuration and the drag of main body. Then the interference factor is derived as the ratio of drag on the complete configuration to drag on the main body. Second order perturbation theory of Van Dyke is used to compute the pressure distribution and resulting wave...

A supersonic zero-lift drag computer program for complex missile- like body shapes has been developed. A mixed method has been developed for wave drag predicting. At first, the supersonic Area-Rule concept is used to predict the drag of complete configuration and the drag of main body. Then the interference factor is derived as the ratio of drag on the complete configuration to drag on the main body. Second order perturbation theory of Van Dyke is used to compute the pressure distribution and resulting wave drag. of main body. The effect of the boundary layer on wave drag can be assessed by adding calculated displacement thickness to the physical areas of main body. Finally, the wave drag of complete configuration is obtained by product of wave drag of main body and interference factors. The friction drag and displacement thickness of main body is direct computed by the method of Whitfield. The friction drag of wing and fin, the base drag of body are obtained from empirical methods. Comparisons of present results with experiments for some configura- tions indicate that the accuracy of ninety percent can be obtained for most conditions.

本文介绍了一种导弹类型超音速复杂组合体零升阻力计算方法。此方法先用面积律求取干扰因子和用二级理论计算主弹体的波阻,再用积分关系式解法求取湍流边界层位移厚度,并用它对波阻进行修正。摩阻、底阻和附加物的阻力计算则采用经验方法。计算结果表明,此方法有相当好的准确性,而且适用范围广。

 
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