一般超音速过渡区气动特性的桥函数方法

桥函数方法已经成功应用于高超音速过渡区气动力计算,但其在一般超音速过渡区领域的适应性问题还缺乏研究.通过DSMC方法,研究适用于计算一般超音速飞行器的过渡区气动力系数的桥函数方法.经过对不同马赫数和不同努森数条件下,圆柱和钝头双楔体过渡区绕流的计算,发现erf-log桥函数方法在计算一般超音速过渡区气动力系数方面具有很好的精度.该结论在把桥函数方法推广到马赫数较低的亚轨道飞行器的过渡区气动力计算方面,具有一定的参考意义.     

交叉三角形波纹板流道在过渡流状态下的传热与阻力特性

交叉三角形波纹板流道中流动常处于过渡态。本文研究了交叉波纹板中的周期性完全发展流动及热传递。利用周期性降低几何流道的复杂性以及简化模拟对象。为了模拟这个拓扑结构中的过渡流,利用了已经验证的低雷诺数k-ε,湍流模型来说明流动中的湍流流动。得到了三维复杂计算区的温度、速度以及湍流场。计算了在恒壁温和恒热流密度两种边界条件下的摩擦系数和平均Nusselt数及其与雷诺数的关系。湍流中心从上层壁面的波纹处移向下层壁面的波纹处并逐步增强。     

高超声速分离-再附流动峰值热流的模型理论

具有大尺度分离区的高超声速分离-再附流动中会在再附点后产生极大的热流峰值.通过分析再附点后局部区域的流动和传热特征,提出了斜驻点-三层结构模型理论框架.继而将此理论框架应用于中低Reynolds数的高超声速压缩拐角流动,提出了其再附点局域流动的外缘参数的工程求解方案,给出了对应的峰值热流值,并与数值计算结果做了对比验证...     

高超声速三维热化学非平衡电离流动计算研究

研究发展了一种计算高超声速三维热化学非平衡电离流动的数值方法。真实气体热力学状态是通过平动-转动温度和电子-振动温度来模拟。对零攻角轴对称钝锥体和有攻角钝锥体的高超声速电离流动,采用隐式有限体积法NND格式,数值求解NS方程。     

微小单锥体热沉射流流动及换热特性研究

射流冷却是高热流密度换热的有效方法之一,射流尺度及热沉结构均对换热性能产生显著影响。本文对一种微小单锥体热沉结构,采用Realizableκ-ε湍流模型对热沉表面流动及换热特性进行研究,并进行实验验证。结果表明:在本文研究范围内(锥体直径为5 mm,锥体高度h分别为5 mm、7.5 mm和10 mm,射流雷诺数Re_j分别为2000、4000、6000、8000),在锥体附近产生环形的带状区域。Re_j对区域半径影响显著,当Re_j分别为2000、4000、6000、8000时,对应的区域半径分别约为5 mm、12 mm、18 mm、23 mm。根据流动结构和压力分布特点,单锥体热沉表面可分为四个区域,分别为驻点区、斜掠区、折冲区和附壁射流区,锥体热沉局部努塞尔数与局部压力系数分布相对应.与h=5mm和h=10 mm的热沉相比,当h=7.5 mm时热沉对流换热效果较好,平均努塞尔数可提升3.4%~6.2%,在h=7.5mm、Re_j=8000的情况下,当热流密度小于0.192~0.324 MW/m~2时,锥体热沉可对热源实现有效散热。     

迎风TVD格式在粘性流计算中的应用研究与改进

首先以高超声速钝楔绕汉热流计算和Ｍ∞＝２．０、激波角θ＝３２．５８°的平板激波附面层干扰分离流动计算,研究了迎风ＴＶＤ格式的粘性特性、发现即使在很小的物面网格下,原有格式计算驻点热流仍较实验和文献结果低,激波附面层干扰的分离区小于实验值,原因主要在于熵修正公式。针对这些不足提出了新的熵修正公式,用改进后的格式重新计算,得到了与实验符合较好的结果。最后用改进的格式对分离流动的壁面温度控制效应进行了研     

吸气式高超声速飞行器气动力气动热的数值模拟方法及应用

对吸气式高超声速飞行器而言,物面热流和摩阻的准确预测对飞行器设计及安全十分关键.介绍采用CFD准确预测气动力和气动热的方法,包括流动的控制方程、湍流模型及湍流的先进壁面函数边界条件,介绍流动的数值求解方法.对典型超声速层流和湍流流动的摩擦阻力和热流进行详细的验证与确认,考察CFD工具在使用先进壁面函数边界条件后,湍流计算的法向网格无关性能力.对设计的一种吸气式高超声速飞行器的气动力和气动热进行数值模拟,为飞行器的气动设计及热防护提供了可靠的数据.     

细光束在钝锥体外流场中的追迹

飞行的钝锥体外流场在密度分布上具有强烈非均匀性,这将导致其传输的细光束在远场靶面上产生偏移,从而影响其光学探测系统的作用精度。探讨并给出了任意折射率分布介质中的光线追迹方法。利用该方法对钝锥体外流场中的细光束路径进行了计算。计算结果表明：在所选位置上,锥体外流场对光线的出射角有明显的影响,但不是特别剧烈;当钝锥体表面加冷却源后,流场密度梯度变化加大,光束出射角的脱靶量明显加大。校正外流场为分析钝锥体上光学系统引入的目标脱靶量提供参考依据。     

亚声速圆锥扩压器内紊流可压缩流动的数值计算

本文应用涡量-流函数作为主要变量对粘性流体流动进行求解.理论上可适用于有回流和无回流的流动情况.为了验证本方法的可靠性,特对小扩张角圆锥扩压器内可压缩粘性流体的流动进行了计算.由于只涉及无回流的紊流边界层发展过程,在数值计算中采用了Prandtl混合长度假说,同时考虑了进口不均匀速度分布.计算结果与文献[4]中实验数据相比较是相当吻合的.这说明本方法可用于一般无分离流动的圆锥扩压器的设计计算.     

微重力环境下无限长柱体内角毛细流动解析近似解研究

应用同伦分析法研究无限长柱体内角毛细流动解析近似解问题,给出了级数解的递推公式.不同于其他解析近似方法,该方法从根本上克服了摄动理论对小参数的过分依赖,其有效性与所研究的非线性问题是否含有小参数无关,适用范围广.同伦分析法提供了选取基函数的自由,可以选取较好的基函数,更有效地逼近问题的解,通过引入辅助参数和辅助函数来调节和控制级数解的收敛区域和收敛速度,同伦分析法为内角毛细流动问题的解析近似求解开辟了一个全新的途径.通过具体算例,将同伦分析法与四阶龙格库塔方法数值解做了比较,结果表明,该方法具有很高的计算精度.     

Variation character of stagnation point heat flux for hypersonic pointed bodies from continuum to rarefied flow states and its bridge function study

This paper is a research on the variation character of stagnation point heat flux for hypersonic pointed bodies from continuum to rarefied flow states by using theoretical analysis and numerical simulation methods. The newly developed near space hypersonic cruise vehicles have sharp noses and wingtips, which desires exact and relatively simple methods to estimate the stagnation point heat flux. With the decrease of the curvature radius of the leading edge, the flow becomes rarefied gradually, and viscous interaction effects and rarefied gas effects come forth successively, which results in that the classical Fay-Riddell equation under continuum hypothesis will become invalid and the variation of stagnation point heat flux is characterized by a new trend. The heat flux approaches the free molecular flow limit instead of an infinite value when the curvature radius of the leading edge tends to 0. The physical mechanism behind this phenomenon remains in need of theoretical study. Firstly, due to the fact that the whole flow regime can be described by Boltzmann equation, the continuum and rarefied flow are analyzed under a uniform framework. A relationship is established between the molecular collision insufficiency in rarefied flow and the failure of Fourier’s heat conduction law along with the increasing significance of the nonlinear heat flux. Then based on an inspiration drew from Burnett approximation, control factors are grasped and a specific heat flux expression containing the nonlinear term is designed in the stagnation region of hypersonic leading edge. Together with flow pattern analysis, the ratio of nonlinear to linear heat flux W _r is theoretically obtained as a parameter which reflects the influence of nonlinear factors, i.e. a criterion to classify the hypersonic rarefied flows. Ultimately, based on the characteristic parameter W _r , a bridge function with physical background is constructed, which predicts comparative reasonable results in coincidence well with DSMC and experimental data in the whole flow regime.     

钝锥绕流流动稳定性分析与转捩预报

研究了超音速钝锥绕流的稳定性和转捩点预报的数值计算方法,首先采用Euler方程求解钝锥绕流基本流场,用所得到的物面压力分布作为粘性边界层的外缘压力分布,给出了基本流场的初值;然后应用反迭代法与边界层渐近匹配的方法求解了钝锥边界层的稳定性方程,得到了钝锥边界层转捩数据.该方法可提高计算精度,节约计算时间.     

New scaling law for the decay exponent of bimolecular reactions in unbounded transitional flows

We propose a new scaling law for global kinetics of the stoichiometric reaction A+B-->P in unsteady, transitional flows. We find in the nonlinear flow regime the decay as approximately t(-alpha) where alpha is related to a space-time scaling parameter psi as alpha proportional, variant psi(m), for the considered parameter range m=0.067. In the linear flow regime, we find that the maximum is alpha approximately 2/3 for psi approximately 1. The proposed scaling law should be useful for linking dynamical subgrid processes with reaction kinetics in a variety of transitional flow systems.     

DNS of turbulent flow with hemispherical wall roughness

The present study of the effect of roughness density on the mean flow turbulence parameters is motivated by the need for new generation of boundary conditions for multiphase computational multiphase fluid dynamics (CMFD) models applied to boiling flows. Effect of roughness element density on the turbulent flow in a channel is quantified through direct numerical simulations (DNSs). The Navier--Stokes equations are solved using finite element method and bubbles are approximated as rigid near-hemispherical obstacles at the wall. Six different cases were analysed including channel flow with smooth wall and channel flow with rough wall for five different bubble nucleation site densities. Friction factor and the law of the wall was calculated and compared with the previously published results. Existing correlations for nucleating bubble site density dependency on a wall heat flux were used to obtain a relation between the heat flux and the friction factor, leading to the law of the wall dependency on the heat flux. This separate effect study provides new guidelines on how the heat flux in subcooled boiling regime affects the turbulence behaviour near the wall and guides the computational fluid dynamics model development for boiling two-phase flows.     

Calculation of the heat flux in a plane layer of a diatomic gas with allowance for energy accommodation

The heat flux in a plane layer of a diatomic gas is calculated in an approximation linear in temperature difference. General expressions (independent of the form of the kinetic equation and the solution method) for the heat flux as a function of the energy accommodation coefficient are derived. The accuracy of heat flux calculation versus the number of terms in the distribution function is estimated with the method of semispatial moments.     

Experimental study on supersonic film cooling on the surface of a blunt body in hypersonic flow

The experimental study focuses on the heat flux on a double cone blunt body in the presence of tangential-slot super- sonic injection into hypersonic flow. The tests are conducted in a contoured axisymmetric nozzle with Mach numbers of 7.3 and 8.1, and the total temperature is about 900 K. The injection Mach number is 3.2, and total temperature is 300 K. A constant voltage circuit is developed to supply the temperature detectors instead of the normally used constant current circuit. The schlieren photographs are presented additionally to visualize the flow and help analyze the pressure relationship between the cooling flow and the main flow. The dependence of the film-cooling effectiveness on flow parameters, i.e. the blow ratio, the convective Mach number, and the attack angle, is determined. A semi-empirical formula is tested by the present data, and is improved for a better correlation.     

展向凹槽及泄流孔对高超声速平板边界层转捩影响的试验研究

针对展向凹槽和泄流孔对高超声速钝平板边界层转捩的影响,在中国空气动力研究与发展中心F2 m激波风洞(FD-14A)开展了试验及初步的计算与理论研究.试验的来流马赫数为6、单位雷诺数为3.3×107/m,平板的前缘半径为1 mm,攻角为–4°.在距平板前缘110 mm处布置三组不同的二维展向凹槽,凹槽的宽度与深度分别为凹槽1(2.5 mm,1 mm)、凹槽2(3.75 mm,1.5 mm)、凹槽3(5 mm,2 mm),同时凹槽1的两端可以打开泄流孔,记为凹槽4,不含凹槽时的光滑平板情况记为凹槽5或平板.采用热流传感器测量了不同情况下平板中心线的热流分布,测量结果显示,光滑平板情况在x≈340 mm处开始转捩,在x≈425 mm处转捩接近完成.凹槽导致平板边界层的转捩位置提前,且随着凹槽宽度及深度的增加,对转捩的促进作用增强,转捩位置向上游移动.凹槽1增加泄流孔后(凹槽4)其热流分布及转捩位置与光滑平板情况基本一致.边界层流动完全转捩为湍流后,各情况下的热流差别较小,表明不同规格的凹槽只影响转捩过程中的热流分布,对转捩完成后的湍流壁面热流影响较小.数值计算(CFD)结果显示,泄流孔导致了被动抽吸,试验结果显示凹槽两端的泄流孔抽吸效应抵消了凹槽对平板中心线边界层转捩的促进作用.采用线性稳定性理论(LST)及最优扰动方法分析了光滑钝平板情况的流动失稳机制.LST结果显示,本文平板流动不存在Mack第一模态、第二模态失稳,因此传统的模态失稳机制无法解释试验中观测到的转捩现象.最优扰动计算显示,平板流动存在较强的非模态失稳,可以定性解释观测到的转捩现象.     

HEAT TRANSFER IN HIGH-PRESSURE COMPRESSOR GAS TURBINE INTERNAL AIR SYSTEMS: A ROTATING DISC-CONE CAVITY WITH AXIAL THROUGHFLOW

This article reports on heat transfer measurements made on a rotating test rig representing the internal disc-cone cavity of a gas turbine high-pressure (H.P.) compressor stack. Tests were carried out for a range of flow rates and rotational speeds at engine representative nondimensional conditions. The rig also had a central drive shaft, which could rotate in the same direction as the discs, contrarotate relative to the discs, or remain static. Measurements of heat transfer were obtained from a conduction solution method using measured surface temperatures as boundary conditions. Results from the outer surface of the cone are in reasonable agreement with theoretical predictions for the heat transfer from a free cone in turbulent flow. The heat transfer measurements from the inner surface of the cone reveal two regimes of heat transfer: one governed by rotation, the other by action of the throughflow. In the rotationally dominated regime, the heat transfer from the inner surface of the cone is higher for a co-rotating shaft than for either a static or contra-rotating shaft. In the throughflow-dominated regime the heat transfer shows little consistent dependence on the direction of shaft rotation. Tests carried out at different values of surface-to-fluid temperature difference add support to the hypothesis that in the rotationally dominated regime the heat transfer occurs through a process of free convection, where the buoyancy force is induced by rotation. The heat transfer from the disc is significantly lower than that from the inner surface of the cone and more or less insensitive to the sense of shaft rotation. The disc average Nusselt numbers show similar behavior to those from the inner surface of the cone and suggest that the disc heat transfer too is governed either by rotationally induced buoyancy or by the axial throughflow.     

Hybrid nanofluid flow over two different geometries with Cattaneo–Christov heat flux model and heat generation: A model with correlation coefficient and probable error

The authors scrutinize the steady, MHD flow of SiO₂−MoS₂/water hybrid nanofluid towards two different geometries i.e. a wedge and a cone. The Tiwari and Das model is implemented with a generalized–Fourier's model, popularized as Cattaneo-Christov heat flux model. Analysis of heat transfer also incorporates the effects of suction, heat generation and thermal radiation. To showcase the relationship between engineering quantities and pertinent parameters involved in the study, the correlation coefficient for heat transfer coefficient and the skin friction coefficient is computed followed by the computation of probable error and statistical declaration. Similarity transformations are utilized to remodel the constitutive laws of flow in non-dimensional form. Numerical computation of non-linear, coupled O.D.E.’s is performed with the support of the Runge-Kutta-Fehlberg scheme and shooting method. Graphical and tabular illustrations of computed results are provided to report the variation in flow properties with the fluctuation in physical parameters. In both cases, i.e. flow close to a wedge and a cone, the temperature of hybrid nanofluid enhances on intensifying the thermal radiation and experiences a decrement with thermal relaxation parameter and magnetic field. Rising values of the suction parameter, thermal relaxation parameter, and thermal radiation cause increment in heat transfer coefficient. Interestingly, it was spotted that the heat generation parameter has contrary effects on temperature distribution over the two geometries.