1)transonic flow跨音速流
1.The transonic flows in the convergent-divergent nozzles with the secondary flow are computed by the definite element method.本文用有限元法数值分析带二次流可调收—扩喷管跨音速流动，紊流粘性采用ｋ—ε双方程模型来描述，并利用加权余量法中的Ｇａｌｅｒｋｉｎ法建立有限元方程，求解可压缩粘性流体流动Ｎ－Ｓ方程，喷管壁面采用壁面函数。
2.To compute transonic flows over a complex three dimensional aircraft configuration,a viscous/ inviscid interaction method was developed by coupling an boundary-layer solver with Eluer solver.采用求解Euler方程结合附面层修正的方法在结构网格上对翼身组合体跨音速流场进行了数值模拟。
英文短句/例句
1.Credibility Analysis of RAE2822 Airfoil Transonic Flow ComputationRAE2822翼型跨音速流动CFD计算的可信度分析
2.VARIATIONAL PRINCIPLE WITH VARIABLE DOMAIN DISCO-NTINUOUS FINITE ELEMENT METHOD FOR TRANSONICFLOW AND DETERMINING AUTOMATICALLY THEPOSITION AND SHAPE OF THE SHOCK WAVES跨音速流场的变域变分间断有限元解法及激波位置的自动捕获
3.Stability of Transonic Shocks in Supersonic Flow Past a Wedge;超音速绕流中产生的跨音速激波的稳定性研究
4.NUMERICAL INVESTIGATION OF FLOW FIELD IN A 1.5-STAGE TRANSONIC COMPRESSOR1.5级跨音速压气机内部流场数值分析
5.Gridless Method for the Simulation of Transonic and Supersonic Flows;无网格方法在跨音速、超音速流场数值模拟中的应用
6.Numerical Research on Effects of Splitter Blades on a Transonic Centrifugal Compressor Impeller跨音速离心压缩机叶轮分流叶片的数值研究
7.trisonic aerodynamics三音速(亚音速、跨音速 、超音速)空气动力学
8.NUMERICAL SIMULATION ON UNSTEADY TIP LEAKGAE FLOW IN A TRANSONIC AXIAL FAN ROTOR某跨音速轴流压气机转子叶顶泄漏流的非定常特征
9.transsuper aerodynamics跨音速和超音速空气动力学
10.The aerodynamic force is solved with the second order approximation method for transonic small disturbance potential flow.用跨音速小扰动势流的二级近似方法求解气动力;
11.Prediction and Analysis of Fluctuating Pressure at Transonic Mach Numbers and Nonlinear Characteristic of RB Convection System;跨音速脉动压力及RB对流系统非线性特征的预测与分析
12.Large eddy simulation of mixing process in chemical oxygen-iodine lasers化学氧碘激光器内流场亚跨超音速混合的大涡模拟研究
13.Simulation of Transonic Unsteady Flow with Improved Unstructured Dynamic Grid Method用改进非结构动网格方法模拟跨音速非定常绕流
14.Unsteady loss analyses of the flow in single-stage transonic compressor单级跨音速压气机内流场的非定常模拟及损失分析
15.UNSTEADY RESPONSE OF TIP LEAKAGE FLOW TO DISCRETE MICRO TIP INJECTION IN A TRANSONIC AXIAL COMPRESSOR AND ITS EFFECT ON STABILITY ENHANCEMENT跨音速轴流压气机叶顶间隙泄漏流对微喷气的非定常响应机制和扩稳效果研究
16.Empirical results are needed in the transonic Mach regime.在跨音速马赫数范围内需要经验结果。
17.In this paper, the calculations of two-phase transonic nozzle flow are completed by a time-dependent method for the gas governing equations and by a characteristic mothod for the particle governing equations.对气相和颗粒控制方程分别应用时间相关法和特征线法,完成了两相跨音速喷管流场的计算。
18.Numerical Investigation on the flow in a stage of Transonic Centrifugal Compressor with Vaned Diffuser Coupling with Different Configuration of Volute单级跨音速离心压缩机叶片扩压器和不同蜗壳形式耦合的内部流动数值研究
相关短句/例句
transonic flow跨音速气流;跨音速流
3)transonic flow跨音速流动
1.Application of all\|speed algorithm in turbulent transonic flows calculations;全速解法在湍流跨音速流动中的应用
2.Using the improved method we studied inviscid and viscous transonic flow in turbomachinery based on Euler and Navier Stokes equations.计算结果表明，本方法是透平机械内部跨音速流动计算的强有力的手段。
3.A transonic flow mathematic model based on standard k-εturbulence model was proposed to investigate the mixing flow behaviors of primary and secondary fluid in steam ejector.为研究水蒸气喷射泵内部工作蒸汽与被抽气体的流动和混合行为,基于标准k-ε模型,建立了描述跨音速流动的数学模型。
4)transonic flow field跨音速流场
5)transonic stream tube跨音速流管
6)transonic diffuser grid flow跨音速叶栅流动
1.The paper describes the application of Extension o f the Finite Area Time Marching Method in the calculation of transonic diffuser grid flow. 论述了时间相关有限差分法在跨音速叶栅流动计算中的应用,并以具有代表性的跨音速压气机叶栅流场的计算和图样的制取为例,附以程序编制及其流程图,详细地讲解了计算程序的具体操作。
延伸阅读
跨音速飞行 飞行器以马赫数0.8～1.2的速度飞行(见飞行速度)。飞行器从亚音速到超音速或从超音速到亚音速飞行必须经过跨音速区。跨音速区从飞行器表面上某点气流出现音速的所谓临界速度起到整个流场都是超音速为止，是飞行器表面的气流既有亚音速又有超音速的"混合流动"区，在理论上属混合型方程。这时马赫数和雷诺数都影响飞机的空气动力特性。飞机达到临界速度时，其表面形成激波并随马赫数增大而发展。激波后压力剧增，导致翼面附面层内气流分离。激波与附面层又相互作用。激波产生波阻，使阻力比亚音速时增大若干倍，升力减小，压力中心后移，力矩突变，飞机可能出现振动或颤振（见气动弹性力学）。升降舵和副翼等操纵面效率大为降低，而其铰链力矩大增。纵向、横向和航向平衡受到局部影响，尤其是纵向平衡，还容易出现蹬舵反倾斜现象。低空大表速、高空大马赫数的跨音速飞行容易出现自动倾斜，或称翼下冲。此外，高度表、速度表、马赫数表和升降速度表指针因激波而晃动，高度表指示误差可达700～800米，这些都会给飞行员带来不便。 超音速飞机越过跨音速的时间短暂，这些影响还不致给驾驶员带来麻烦。持久的跨音速飞行不仅阻力剧增，耗油量大，而且上述不利影响还会使驾驶员操纵困难。现代很少有专为跨音速飞行设计的飞机。克服跨音速飞行的不利影响的措施是使用小展弦比、小厚度比的后掠机翼和研究超临界机翼以及机身按面积律修形等。
