高超声速飞行器复杂外形转捩预测

采用k-ω-γ转捩模式对某新型飞行器外形的典型流动特征和边界层失稳特性进行了分析.研究结果表明,横流是影响飞行器大面积转捩的主要因素.随着高度增加,来流Reynolds数减小,迎风面和背风面的转捩起始位置均向下游移动.随着攻角增加,头部附近背风面的展向压力梯度增大,横流效应增强,转捩起始位置向上游移动;另一方面攻角增加导致头部激波增强,波后迎风面密度显著增大,边界层外缘Reynolds数增大,导致迎风面转捩提前发生.0°攻角下背风面中心线附近由压缩面诱导的流动分离导致转捩提前,产生"凸"字型转捩型线,5°攻角时该流动分离发生于转捩之后,"凸"字型转捩型线消失.      

Reynolds数22 000的孤立方柱绕流的大涡模拟

方柱绕流是典型的钝体绕流问题,蕴含了丰富的流体力学现象,对这类流动的准确预测面临着诸多挑战.采用自主发展的大涡模拟程序,对来流Mach数M=0.3,Reynolds数Re_D=22 000的绕孤立方柱流动进行了细致模拟,亚格子模型使用动力涡黏模型.对计算结果的分析表明,大涡模拟所得的平均流场及Reynolds应力分布与已有实验数据和直接数值模拟结果均吻合较好,验证了预测结果的可靠性;在此基础上对瞬态流场进行了研究,展示了计算条件下方柱绕流分离转捩及尾迹区旋涡交替脱落形成Karman涡街的全过程,为更细致的流动机理探索奠定了基础.      

磷光热图技术在常规高超声速风洞热环境实验中的应用

通过采取快速插入、建立同步采集系统等措施,在中国航天空气动力技术研究院FD-07常规高超声速风洞建立了磷光热图技术,并成功地获得了平板三角翼模型表面热流分布.基于实验结果,初步分析了来流Reynolds数等参数对三角翼表面热流分布的影响.结果表明,三角翼外形中心线处转捩靠后,两侧转捩靠前,且随着来流Reynolds数的增加,转捩位置进一步前移.总的来说,磷光热图技术能够直观地显示流动转捩发生的位置以及转捩后湍流区的形状,为高超声速飞行器热防护设计提供了一种新的技术途径.      

基于温敏漆技术的圆锥高超声速大攻角绕流背风面流动结构实验研究

高超声速流动中, 大攻角下圆锥背风面边界层会存在流动分离与再附、边界层转捩等多种流动现象, 进而对圆锥表面温度分布产生显著的影响。为了对这一复杂流动规律及其对表面温升分布的影响进行讨论, 研究基于温敏漆技术, 得到了在Mach数为6的低湍流度来流条件下, 攻角为10°的圆锥背风面温升分布结果。通过对不同位置、不同方位角处温升分布曲线的分析, 对大攻角下圆锥背风面边界层流动发展过程及不同发展阶段的流动特征进行了讨论。同时, 通过对来流总压的调节, 得到了不同Reynolds数下的圆锥背风面温升分布结果, 总结了Reynolds数对流动的影响规律。研究发现, 高超声速大攻角圆锥背风面边界层流动发展过程中会依次出现层流分离、定常横流涡影响、转捩以及湍流分离与再附等流动特征, 而在不同的Reynolds数下, 各个流动特征产生影响的范围不同, 随着Reynolds数的降低, 层流范围和定常横流涡影响范围均有所增加, 而从观察到横流影响到转捩开始发生的范围基本相同。      

B-C转捩模型的DDES方法模拟转捩大分离流动

根据零压力梯度平板的实验数据对B-C转捩模型中的经验关联式进行标定.标定后的B-C转捩模型在进口湍流度较低的平板算例上可以提供更合理的转捩预测结果.但受限于RANS方法自身特性，B-C转捩模型对转捩后出现的大分离流动计算可靠性较差.结合延迟分离涡模拟SA-DDES方法和B-C转捩模型，发展了转捩-延迟分离涡模拟BC-DDES方法.三维S-K平板的数值模拟表明，BC-DDES方法能得到与B-C转捩模型一致的转捩结果.三维圆柱绕流的数值模拟表明，BC-DDES方法得到与实验符合的平均阻力系数和表面压力分布，并且计算花费比tHRLES方法少.     

叶型几何设计弱化叶片外表面换热的作用

本文采用γ-Re_θ湍流转捩模型,数值模拟了两组不同叶型的涡轮叶栅表面的表面换热系数。结果证明:1)数值计算正确地预测了转捩发生位置,保证了表面换热系数模拟的可靠性;2)由于叶片型线的差异,叶片表面流动的转捩位置也不同。控制叶片表面边界层流动状态,推迟流动转捩,能够降低叶片热负荷。在相同进、出口气流条件下,选择不同的叶栅造型参数,可以调整所产生的涡轮叶型,从而增强或弱化叶片表面的换热。     

分隔板偏角对圆柱受力和脱涡频率的影响

钝体后安装分隔板是一种有效的被动控制技术,本文采用有限体积法对非稳态二维层流下的圆柱-分隔板结构绕流进行了数值计算。研究了中等雷诺数（Re=100～500）下,分隔板与来流方向存在夹角时（θ=0°～45°）的圆柱绕流特性。结果表明不同Re数下,圆柱阻力和升力系数等反映流动特性的参数随分隔板偏角而变化;阻力系数最小值对应...     

高超声速椭圆锥边界层横流转捩特性大涡模拟

横流效应显著影响高超声速飞行器的三维边界层转捩过程, 深化对该流动机制的认识有助于提升和改善飞行器气动性能及热力学环境. 针对HIFiRE5椭圆锥绕流问题, 采用大涡模拟方法计算分析了超声速边界层横流转捩特性, 并揭示其中的流动机理. 参考HIFiRE5风洞模型试验条件, 数值模拟中椭圆锥来流入口处施加人工速度扰动以激发边界层内不稳定扰动波, 进而预测了高超声速边界层流动横流失稳、转捩过程等基本流动特征, 并基于转捩热流分布形态对比, 获得了与试验数据基本吻合的计算结果. 研究发现, 椭圆锥中心线流动汇聚形成的流向涡结构非常容易失稳, 另外在中心线及侧缘之间的中部区域存在较强的横流不稳定性, 两种机制共同作用影响边界层转捩过程. 此外, 分析了来流扰动幅值对边界层横流失稳转捩的影响, 并发现静来流条件下, 横流区域出现两组独立的定常横流涡结构, 而强噪声来流条件下, 中心线主涡和中部横流涡均发生失稳转捩, 且在椭圆锥表面形成多峰状的转捩阵面. 最后, 深入分析流场的压力脉动动力学特性, 揭示了三维边界层发生失稳转捩的非线性演化机制.      

基于壁面压力反馈的圆柱绕流减阻智能控制

针对经典圆柱绕流问题,采用深度强化学习方法,提出了基于壁面压力反馈的圆柱绕流减阻闭环主动控制方法,并比较分析了施加控制前后圆柱阻力系数、升力系数及流场的差异.控制系统中,以圆柱壁面上均匀分布的压力探针测得的信号作为反馈,利用多层感知机建立压强信号与吹/吸射流及控制效果的映射关系,即控制策略;通过在圆柱上下表面狭缝施加连续可调的吹/吸射流来进行主动控制.同时,利用深度强化学习中的近端策略优化方法,在大量的学习过程中对该控制策略进行不断调整和优化,以实现稳定减阻效果.在圆柱绕流流动环境搭建方面,采用格子Boltzmann方法建立与深度强化学习模型之间的交互式框架,模拟提取非定常流场条件下圆柱表面的压强信号,并计算实时调整吹/吸射流强度时圆柱表面升力、阻力数据,以评估所选控制策略的优劣.研究表明:雷诺数为100时,主动控制策略能减少约4.2%的圆柱阻力,同时减少约49%升力幅度;同时施加主动控制后圆柱的减阻效果与圆柱回流区长度呈现强相关趋势.此外,不同雷诺数下智能体习得的策略减阻效果不同,雷诺数为200和400时,该主动控制策略能依次减小圆柱阻力17.3%和31.6%.本研究可为后续开展基于...     

考虑对流效应的圆柱绕流气动噪声的预测

采用非稳态雷诺时均(URANS)方程求解圆柱绕流获得近场声源信息,同时运用考虑对流效应的频域声比拟方法,研究了圆柱绕流的气动噪声问题,并考察了不同来流马赫数对辐射声压的影响。结果表明:卡门涡的脱落导致圆柱阻力系数频率为升力系数频率的两倍;较大的升力系数脉动幅值产生了偶极子源,偶极子源在远场辐射声压中占主导作用,最大辐射声压垂直于来流方向;随着马赫数的增大,对流效应显著增强且辐射声压正比于马赫数的三次方。     

Numerical simulation of flow around a circular cylinder with curved sectional grooves

In a circular cylinder with uniform flow, a sudden decrease in the drag force occurs at a high Reynolds numbers; however, it is known that the same phenomenon occurs at a lower Reynolds number in the case where there exist grooves or roughness on the circular cylinder surface. To clarify the flow characteristics around a circular cylinder in the case of changing the shape of grooves we analyzed the drag coefficient, lift coefficient, turbulent kinetic energy, vorticity and pressure by applying the RNGk-ε turbulent model. The shapes of the grooves were arced, triangulated and curved. The results showed that the separation point for a circular cylinder with curved sectional grooves shifts to the most downstream side and the drag coefficient becomes the smallest among circular cylinders with grooves.     

The influence of heat radiation on mixed convection boundary layer flow of a viscoelastic fluid over a circular cylinder with constant surface temperature

The influence of mixed convection boundary layer flow of a viscoelastic fluid over an isothermal horizontal circular cylinder has been analyzed. The boundary layer equations governing the problem are reduced to dimensionless nonlinear partial differential equations and then solved numerically using Keller-box method. Skin friction coefficient and Nusselt number are emphasized specifically. These quantities are displayed against curvature parameter. Effects of mixed convection parameter and radiation-conduction parameter on skin friction coefficient and Nusselt number are illustrated through graphs and table. The boundary layer separation points along the surface of cylinder are also calculated with/without radiation, and a comparison is shown. The presence of radiation helps to reduce the skin friction coefficient in opposing flow case and enhances it for assisting flow case. The increase in value of radiation-conduction parameter helps increase the value of skin friction coefficient and Nusselt number for viscoelastic fluids. The boundary layer separation delays due to thermal radiation.     

Effect of the number of grooves on flow characteristics around a circular cylinder with triangular grooves

In the flow around a circular cylinder, a sudden decrease in the mean drag coefficient occurs at a high Reynolds number, but the same phenomenon occurs at a lower Reynolds number in the case where there exist grooves or roughness on the cylinder surface. In this paper, in order to make clear the flow characteristics around a cylinder with 20, 26 and 32 triangular grooves, the mean drag coefficient, pressure distribution, velocity distribution and turbulence intensity distribution were measured. Moreover, the flow around the cylinder was analyzed by applying the RNGk − ɛ turbulent model, and the surface flow pattern was investigated using the oil-film technique. From these results, it was found that a sudden decrease in the mean drag coefficient of a cylinder with 32 triangular grooves occurs at a lower Reynolds number compared with 20 and 26 triangular grooves.     

Laminar-turbulent transition in Hagen–Poiseuille flow of a real gas

The effect of gas non-ideality on the laminar-turbulent transition is studied experimentally as the flow in a long circular tube at room temperature. The gases SF₆ and Ar, differing significantly in the value of the second virial coefficient, were chosen for this study. Experiments were carried out by varying the pressure at the tube inlet (the maximum pressure of 10⁵ Pa) and at the tube outlet up to the chock flow (formation of a supersonic flow at the outlet). The difference between the critical Reynolds numbers in the flow of SF₆ and Ar was found. The largest difference was observed for the maximum pressures; with a decrease in pressure, the critical Reynolds numbers become closer. The conclusion is an effect of the non-ideal character of gas exists on the laminar-turbulent transition in Hagen–Poiseuille flow. Some experiments were suggested to confirm this conclusion.     

Flow separation behind a rib in a channel with laminar flow

Visualization data and results of combined measurements of flow quantities in flow with separation past a rib at nominally laminar regime of channel flow are reported. In the separation region, the flow is found to be essentially three-dimensional and unsteady, exhibiting a distinct cellular structure and flow zones with transverse motion. It is shown that the rib-induced flow separation gives rise to low-frequency fluctuations of flow velocity and initiates the turbulence transition in the channel flow. The critical Reynolds number at which flow instability starts developing in the channel is estimated. It is shown that at Reynolds numbers higher than the critical Reynolds number the linear integral scale of flow velocity fluctuations in the channel is defined by the duct size.     

Effect of groove shape on flow characteristics around a circular cylinder with grooves

In the flow around a circular cylinder, a sudden decrease in the drag force occurs at a high Reynolds number, but the same phenomenon occurs at a lower Reynolds number in the case where there exist grooves or roughness on the circular cylinder surface. In this paper, in order to make clear the flow characteristics around a circular cylinder in the case of changing the shapes of grooves, the drag coefficient, pressure distribution, velocity distribution and turbulent distribution were measured. Moreover the flow around the cylinder was analyzed by applying the RNGk · ∈ turbulent model, and the surface flow pattern was investigated using the oil-film technique. From these results, it is clear that the drag coefficient of a circular cylinder with triangular grooves decreases by about 15% compared with that of a circular cylinder with arc grooves.     

绕圆柱体自由表面磁流体流动和传热的研究

本文对在不同雷诺数下,绕圆柱体的磁流体自由表面流动及传热进行了模拟,分析了磁场对绕流圆柱尾迹和涡分离的影响,获得了两种雷诺数下的电磁力密度、流场和温度场分布。结果表明,磁场不仅影响了流动的形态,而且对湍流有抑制作用,降低了自由表面的更新机制,从而减少了传热能力;在相同的Hartmann数下,相比低雷诺数下的流动换热情况,高雷诺数下的湍流不能被完全抑制,自由表面与尾迹的相互作用也较强,因而自由表面换热也较强。     

电磁力控制湍流边界层分离圆柱绕流场特性数值分析

在亚临界区高雷诺数Re=1.4×105下,采用脱体涡模拟结合湍流分离的方法对弱电解质中电磁力作用下湍流边界层分离圆柱绕流场及其升(阻)力特性进行了数值模拟和分析.结果表明,电磁力可以提高圆柱体湍流边界层内的流体动能,延缓圆柱体湍流边界层的流动分离,减弱圆柱体湍流绕流场中在流向和展向上大尺度漩涡的强度,减小圆柱体阻力时均值及其升力脉动幅值.当电磁力作用参数大于某个临界值后,湍流边界层流动分离消失,在圆柱体尾部产生射流现象,从而电磁力对圆柱体产生净推力作用,出现负阻力现象,而且升力脉动幅值接近于零,出现圆柱体升力消失现象.     

三维内肋管内流态的划分及过渡流判据的实验研究

1前言三维内肋管（见图1）已在许多文献中进行了研究[1～7]。其中文献[7]首次提出了三维内肋管的流态划分问题，指出应按人工粗糙管的流态模式合理地划分为层流区、临界区、过渡流区和旺盛湍流区，且其相邻两区的转换雷诺数都应与肋的几何结构有关。文献[7]主要研究了该管达旺盛湍流时的雷诺判据。本文将着重研究该管达过渡流的雷诺判据。2实验装置与实验方法实验装置如图2所示。实验管几何结构见表1。1．鼓风机2．滤网3LWQ－15型气体涡轮流量变送器（或LZJ－15型玻璃转子流量计）4．XSF－40流量指示积算仪5．调压变压器6．直管段7．UJ…     

Turbulence structures in high-speed air flow along a thin cylinder

Turbulent flow in the axial direction along a cylinder representing a monofilament yarn was reproduced for a relatively wide range of radius Reynolds numbers using direct numerical simulations. In the simulation of the thinnest cylinder, the friction coefficient agreed with a previously published formula. A pair of high- and low-speed streaks was detected around even the thinnest cylinder, whereby it was confirmed that turbulence was sustained according to the analysed turbulence statistics. Even when only a single pair of streaks around the cylinder was detected, the characteristics of the turbulence structures, such as the mean streak spacing based on the viscous length scale, were the same as those in flows over a flat plate. It was found that the friction coefficient changes in a way that maintains the structural characteristics of the flow, consistent with the view that universal characteristics of turbulence structures exist.