高超高焓非平衡流动数值模拟方法研究综述

高性能计算流体力学 (computational fluid dynamic, CFD) 模拟可以与高超飞行试验、高焓地面设备实验研究相互印证, 在热化学非平衡效应研究以及未来高超声速飞行器研制中将发挥更重要的作用. 本文回顾了国内外在热化学非平衡流动CFD研究方面的进展, 概述了相关热化学模型、数值格式研究以及CFD软件研制方面的现状和发展趋势, 最后指出了今后在基础研究、软件开发、模拟应用等方面需要关注的问题. (1) 在热化学模型方面, 常用温度模型并不完全精确, 多振动温度模型具有发展潜力但工程应用受限, 态−态模型更精确但模拟技术尚不成熟, 更为精确的热力学输运模型、有限速率化学反应模型、振动−离解耦合模型以及表面效应模型等是提升热化学非平衡模拟精度的重要物理模型, 值得深入研究; (2) 在数值方法方面, 多物理场耦合模拟是高超热化学非平衡流动CFD研究的热点和趋势, 对CFD方法的鲁棒性和收敛性提出了更高的要求, 值得重点关注和研究, 此外常用数值格式需要针对热化学非平衡流动特征进行适应性改造, RANS方法在热化学非平衡湍流模拟中的计算可靠性仍有待验证; (3) 在数值软件方面, 基于结构/非结构混合网格的数值求解器更加符合工业应用需求, 未来高超数值软件需要具备稳定、鲁棒的多学科、多物理场耦合求解功能, 且能够适应更大网格规模大尺度复杂外形的模拟需求; (4) 可综合应用多种加速技术手段提升热化学非平衡流动数值模拟的计算效率, 计算刚性是热化学非平衡流动数值模拟方法研究的共性基础问题, 刚性消除方法仍需进一步研究和发展.     

高超声速高焓边界层稳定性与转捩研究进展

边界层由层流向湍流的转捩是高超声速飞行器设计面临的重大空气动力学问题. 随着飞行速域与空域的不断拓展, 高超声速高焓边界层中的高温气体效应会使得量热完全气体假设失效, 从而深刻影响流动转捩过程. 相关研究涉及多个学科, 是典型的多物理场耦合问题. 近年来, 随着相关飞行器技术的快速发展, 高超声速高焓边界层转捩问题的重要性越来越得到体现, 相关研究已成为国际上的热点领域. 本文综述相关研究进展, 首先介绍目前常用的高温气体物理模型, 尤其关注热化学非平衡模型, 并介绍激波捕捉、激波装配和边界层方程解等常用的高焓流动求解方法, 以及相关风洞和飞行试验技术的进展. 然后综述高温气体效应对转捩过程中的感受性、模态增长、瞬态增长和非线性作用等的影响的相关研究, 其中流向不稳定性中出现较大增长率的第三模态和超声速模态引起了广泛的研究兴趣. 最后进行总结, 并对未来发展略作展望.      

气体模型对再入飞行器气动力热环境影响的数值研究

复杂外形再入飞行器的设计,需对气动力热环境进行预测,由于不同的气体模型会对预测的结果产生影响,所以气动设计时就必须考虑这一影响.采用热化学平衡气体模型和双温度热化学非平衡气体模型对复杂外形再入飞行器的气动力热环境进行了数值计算;分析了气体模型对气动力、壁面热流等值线、驻点线平动温度、振动温度、组分质量分数等特征量的影响...     

高超声速非平衡流动-辐射特性数值模拟研究

飞行器高超声速飞行过程中所承受对流加热和辐射加热可能具有相当的量级,因此合理准确预测气动加热需要将二者进行综合考虑.文章发展了具有非玻尔兹曼电子能级分布和振动能级分布的高温空气碰撞辐射模型,并耦合一维激波后流动方程计算不同飞行条件下激波后的非平衡流动特性,采用逐线辐射输运模型计算获得激波后非平衡辐射特性、辐射强度和辐射输运通量,深入比较分析了不同飞行高度和马赫数对非平衡流动和辐射输运过程的影响.计算结果表明对于高空高马赫飞行条件,其波后流动存在显著的热力学非平衡、化学非平衡和能级非平衡特征,在近激波区域高振动能级和原子高束缚电子激发态明显低于玻尔兹曼分布.在高空高马赫条件下真空紫外辐射占据主导地位,主要是由高能原子束缚-束缚跃迁造成的.随着高度和马赫数的下降,激波层内气体解离和电离程度降低,原子辐射贡献下降,分子辐射贡献增加,导致红外、可见光和紫外波段的辐射输运增强,真空紫外辐射输运过程减弱.     

基于高温气体效应的磁流体流动控制研究进展

高超声速飞行器强激波后高温气体形成具有导电性的等离子体流场,电离气体为磁场应用提供了直接工作环境.磁流体控制技术利用外加磁场影响激波后的离子或电子运动规律,可有效地改善高超声速飞行器气动特性,在飞行器气动力操控和热环境管理等方面均具有广阔的应用前景; 同时,超导材料及电磁技术的发展又重新推动了这一领域的研究热潮.虽然国内外在高超声速磁流体流动控制领域已开展了一些研究工作,但其实验研究依然极具挑战, 且由于实验条件及测量技术等限制,其压力、热流等参数的测量并没有得出较为系统的结论,因此需要对影响脱体激波距离、热流、压力变化的规律及机理进行深入研究; 同时,数值模拟方法和理论分析也亟待可靠的实验数据来对其进行验证.本综述调研和讨论了基于高温真实气体效应的磁流体流动控制技术研究,主要针对磁流体流动控制的试验技术、数值模拟、理论方法以及流动控制的主要研究方向等进行了总结,并对其发展趋势进行了讨论和展望.     

壁面催化效应对高超声速气动热影响研究

对电弧风洞高焓流动进行模拟时,基于其高温复杂流场特性,对比不同热化学模型、壁面催化条件、流场一体化及分体计算等多种数值计算条件下,电弧风洞内部、出口流场特性及典型模型壁面热流分布。结果表明,模型距离喷管出口较近时,流场分体计算可以提高计算效率,但是模型距离喷管出口较远时,则必须采用一体化计算保证计算精度,数值模拟单温度热平衡模型计算得到的等热流模型表面热流高出双温度热非平衡模型6.99%。同时对电弧风洞高焓流动壁面催化效应开展研究,通过X射线扫描电镜对3组类型热流传感器表面元素成分进行分析,研究热流传感器表面催化属性对气动热测量的影响。结果表明,壁面催化效应会显著增加试验模型表面气动热环境,采用无氧铜基体的塞式量热计进行电弧风洞热流测量时,其表面会被氧化成CuO,数值模拟壁面采用有限催化条件γ=0.022时计算结果与试验结果更接近,也与文献中CuO的催化复合系数匹配。

     

双扩散效应引起的异重流流动

本文研究了在初始密度差极小的情况下由双扩散效应引起的异重流的流动特性。实验表明,具有双扩散效应的双组分异重流在初始密度差不是非常小时,与单组分异量流一样以正比于(△ρ)~(12)的速度作匀速推进;但当初始密度差△ρ趋于零时,双扩散效应使异重流流动依然发生。根据本文提出的理论模型,借助于量级分析法,推得了在不同条件下几种流动阳力之间的关系和异重流推进速度的函数表达式。     

钝体分离流动的实验研究

本文报告了楔形钝体分离流区域的湍流实验,提供了分离区内的时均速度、压力,湍流度和雷诺应力的分布,并对分离区的湍流特征进行了分析。实验表明,分离区内时均速度具有很大的横向梯度。湍流度和雷诺应力的分布曲线很相纵,它们在回流区变化较为平缓,而在混合区,当它们达到极大值之后,便以指数形式向(?)衰减。压力在回流区内变化也不大,但在混合区却具有明显的横向梯度。     

高速双锥绕流中热化学与输运模型影响研究

激波与边界层之间相互作用是高超声速飞行中的常见现象,对飞行器气动性能与飞行安全至关重要.对于高焓来流,流场中通常存在复杂的物理化学现象,此时准确模拟流场中激波边界层相互作用的难度大,相关物理化学建模仍有待进一步考察和研究.本文针对最近文献中纯净空气高超声速双锥绕流实验开展数值研究,分别研究了不同热化学模型与输运模型对壁面压力与热流的影响.热力学模型包括完全气体、热力学平衡和非平衡模型,化学模型包括冻结和非平衡化学模型,输运模型包括经典的Wilke/Blottner/Eucken模型与更加复杂的Gupta/SCEBD模型,以及考虑壁面催化/非催化影响的模型.计算了6个不同算例,涵盖了低焓至高焓来流等不同工况.壁面压力与热流的数值计算结果与实验结果符合较好;对于低焓来流,计算结果主要受到分子内能分布的影响,输运模型对计算结果的影响不大;对于高焓来流,一方面计算结果受到化学反应与壁面催化的影响较大,另一方面不同输运模型对计算结果的影响也更加明显.      

高速双锥绕流中热化学与输运模型影响研究

激波与边界层之间相互作用是高超声速飞行中的常见现象,对飞行器气动性能与飞行安全至关重要.对于高焓来流,流场中通常存在复杂的物理化学现象,此时准确模拟流场中激波边界层相互作用的难度大,相关物理化学建模仍有待进一步考察和研究.本文针对最近文献中纯净空气高超声速双锥绕流实验开展数值研究,分别研究了不同热化学模型与输运模型对壁面压力与热流的影响.热力学模型包括完全气体、热力学平衡和非平衡模型,化学模型包括冻结和非平衡化学模型,输运模型包括经典的Wilke/Blottner/Eucken模型与更加复杂的Gupta/SCEBD模型,以及考虑壁面催化/非催化影响的模型.计算了6个不同算例,涵盖了低焓至高焓来流等不同工况.壁面压力与热流的数值计算结果与实验结果符合较好;对于低焓来流,计算结果主要受到分子内能分布的影响,输运模型对计算结果的影响不大;对于高焓来流,一方面计算结果受到化学反应与壁面催化的影响较大,另一方面不同输运模型对计算结果的影响也更加明显.     

高温气体反应流中的物理力学问题

从气体动理论(kinetic theory of gases)的原理出发导出了非平衡条件下高温气体反应流基本守恒方程组.讨论了出现在方程组中的各种通量在非平衡条件下的意义,给出了从微观出发的输运系数表达式.介绍各种物理动理论与化学动理论过程的微观理论,讨论了在非平衡条件下现有理论的困难.     

上海电视塔球形部件的压力分布和气动力

通过风洞试验研究了上海电视塔上下球体的风压和气动力．结果表明：两球体的压力分布均不同于光滑圆球,阻力比超临界光滑圆球大得多．     

Particle and drop dynamics in the flow behind a shock wave

The results of an investigation of the dynamics of hard particles and liquid drops in the flow behind a transmitted shock wave are presented. From the equation of motion of a particle in the shock wave, relations for the displacement, velocity and acceleration as functions of time and certain velocity-relaxation parameters taking into account the properties of the gas and the aerodynamic drag of the particles are obtained for unsteady flow around the particles at an acceleration of 10³–10⁴ m/s². It is shown that the velocity-relaxation parameters are universal. Approaches to finding the aerodynamic drag of freely-accelerating bodies from the dynamics of their acceleration after being suddenly exposed to the flow are considered. It is established that under these conditions the drop dynamics observed can be well described in terms of the same velocity-relaxation parameters with account for linear growth of the transverse drop size. All the kinematic functions obtained are confirmed experimentally.     

Aerodynamic coefficients of a spinning sphere in a rarefied-gas flow

A three-dimensional rarefied-gas flow past a spinning sphere in the transitional and near-continuum flow regimes is studied numerically. The rarefaction and compressibility effects on the lateral (Magnus) force and the aerodynamic torque exerted on the sphere are investigated for the first time. The coefficients of the drag force, the Magnus force, and the aerodynamic torque are found for Mach numbers ranging from 0.1 to 2 and Knudsen numbers ranging from 0.05 to 20. In the transitional regime, at a certain Knudsen number depending on the Mach number the Magnus force direction changes. This change is attributable to the increase in the role of normal stresses and the decrease in the contribution of the shear stresses to the Magnus force with decrease in the Knudsen number. A semi-empirical formula for the calculation of the Magnus force coefficient in the transitional flow regime is proposed.     

Spatial Evolution of Nonstationary Perturbations in Hamel Flow

The propagation of small perturbations in longitudinally inhomogeneous flows is investigated. The evolution of the perturbations is studied with reference to the radial flow of a viscous incompressible fluid between plane nonparallel walls, the simplest inhomogeneous flow. Using a generalized method of variation of constants, the corresponding boundary-value problem is reduced to an infinite-dimensional evolutionary system of ordinary differential equations for the complex amplitudes of the eigensolutions of a locally homogeneous problem. Physically, the method can be interpreted as a representation of the perturbation evolution process via two concomitant processes: the independent amplification (attenuation) of normal modes of the locally homogeneous problem and the rescattering of these modes into each other on local inhomogeneities of the base flow. The calculations show that reduced versions of the method are promising for describing the linear stage of laminar-turbulent transition in a boundary layer.     

On the Perturbation of Hamel Flow Due to Unevenness of the Channel Walls

A method of analyzing the receptivity of longitudinally inhomogeneous flows is proposed. The process of excitation of natural oscillations is studied with reference to the simplest inhomogeneous flow: the two-dimensional flow of a viscous incompressible fluid in a channel with plane nonparallel walls. As physical factors generating perturbations, the cases of a stationary irregularity and localized vibration of the channel walls are considered. By changing the independent variables and unknown functions of the perturbed flow, the problem of the generation of stationary perturbations above an irregularity is reduced to a longitudinally homogeneous boundary-value problem which is solved using a Fourier transform in the longitudinal variable. The same problem is investigated using another method based on representing the required solution in the form of a superposition of solutions of the homogeneous problem and a forced solution calculated in the locally homogeneous approximation. As a result, the problem of calculating the longitudinal distributions of the amplitudes of the normal modes is reduced to the solution of an infinite-dimensional inhomogeneous system of ordinary differential equations. The numerical solution obtained using this method is tested by comparison with an exact calculation based on the Fourier method. Using the method proposed, the problem of flow receptivity to harmonic oscillations of parts of the channel walls is analyzed. The calculations performed show that the method is promising for investigating the receptivity of longitudinally inhomogeneous flow in a laminar boundary layer.     

Numerical simulation of the ground effect using the boundary element method

As is well known, the lift of a wing passing over the ground becomes larger than that of a wing in a finite air field because of the ground effect. Owing to its special aerodynamic characteristics and applications, the problem of the ground effect has become increasingly common. In this paper some investigations were conducted to calculate the unsteady aerodynamic forces for long and short ground plates by means of boundary element techniques. In order to calculate the pressure variation on a long ground plate, the steady boundary element method was used. However, when using a short ground plate, the boundary element method was modified to treat the unsteady aerodynamic phenomena. Experimental studies were also made for both ground plates to confirm the validity of the numerical results. At low angles of attack the qualitative behaviour of the unsteady aerodynamic pressure on both ground plates was well predicted by the boundary element methods and qualitative agreement is found between the calculated and measured results. © 1997 John Wiley & Sons, Ltd.