International Journal of Heat and Fluid Flow最新文献_第6页

Three-dimensional proper orthogonal decomposition reduced-order model of the global atmospheric climate 全球大气气候的三维适当正交分解降阶模型

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-18 DOI: 10.1016/j.ijheatfluidflow.2026.110253

Vassili Kitsios , Laurent Cordier , Terence J. O’Kane

A reduced-order model (ROM) of the global atmosphere is developed by projecting the hydrostatic equations of motion onto three-dimensional proper orthogonal decomposition (POD) modes. This approach transforms a system of partial differential equations dependent upon time and space, into a system of ordinary differential equations dependent upon only time and POD mode index. This massively reduces the dimensionality of the problem. Here we adopt the Climate Analysis Forecast Ensemble reanalysis dataset (CAFE-60), comprising of 96 realisations of the dynamically coupled atmosphere and ocean each month. Two POD bases are calculated from the atmospheric data, one for the velocity vector field, and another for the scalar temperature field. The POD ROM coefficients are calculated using a regression approach, with model errors accounted for via stochastic parameterisation. Temporal integrations of the POD ROM with dynamically coupled temperature and velocity fields are undertaken over a recent 40-year period. The statistical properties of the underlying data are broadly reproduced within the resolved modes for a range of truncation levels. Additionally, as more modes are retained in the POD ROM, the correlation of surface variance maps between the underlying data and the spatially reconstructed POD ROM output, approaches unity. The POD ROM coefficient learning and temporal integrations are completed in minutes on a laptop, as compared to the months of supercomputer time required to generate CAFE-60.

将流体静力运动方程投影到三维固有正交分解模式上，建立了全球大气的降阶模型（ROM）。该方法将依赖于时间和空间的偏微分方程组转化为仅依赖于时间和POD模态指标的常微分方程组。这大大降低了问题的维度。本文采用气候分析预报集合再分析数据集（CAFE-60），该数据集包括96个大气和海洋每月的动态耦合实现。根据大气数据计算了两个POD基，一个用于速度矢量场，另一个用于标量温度场。POD ROM系数使用回归方法计算，通过随机参数化计算模型误差。在近40年的时间里，对POD ROM与动态耦合的温度场和速度场进行了时间积分。基础数据的统计特性在截断水平范围内的解析模式内广泛再现。此外，由于POD ROM中保留了更多的模式，底层数据与空间重构POD ROM输出之间的地表方差图的相关性趋于统一。POD ROM系数学习和时间积分在笔记本电脑上几分钟就能完成，而超级计算机需要几个月的时间才能生成CAFE-60。

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引用次数: 0

Multi objective heat dissipation space optimization feedback control algorithm based on threshold triggering 基于阈值触发的多目标散热空间优化反馈控制算法

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-20 DOI: 10.1016/j.ijheatfluidflow.2025.110233

Qian Zhang , Jia Kang , Xing Zhang

With the trend of VR devices toward high-density integration and miniaturization, the collaborative heat dissipation challenges for multiple heat sources in compact spaces have emerged as a critical bottleneck constraining device performance. This study addresses the scientific question of “how to predict the minimal heat dissipation space for high heat flux electronic devices while ensuring safe thresholds for chip junction temperature and exhaust air temperature under coupled thermal-resource conditions in VR devices.” To tackle this, a systematic thermal management framework based on multi-physics coupling was established. This model includes dimensional selection criteria for graphene layers, a one-dimensional steady-state thermal analysis for flow in narrow channels, and thermal diffusion expressions for the MgAl framework. Third, a triple-nested optimization architecture is designed. It leverages coordinated feedback mechanisms across inner-loop multi-physics balancing, middle-loop channel parameter adjustment, and outer-loop fan characteristic optimization to dynamically match thermal performance with spatial constraints. The results demonstrate a 27.2% reduction in the required heat dissipation space volume for typical VR modules. Consequently, this work provides a theoretical tool for the synergistic co-optimization of spatial volume and thermal feasibility under fixed performance constraints in VR thermal management. The proposed threshold-triggered mechanism is also extendable to thermal design in other compact electronics, such as smart wearables and micro machine vision systems.

随着VR设备向高密度集成化和小型化发展，紧凑空间内多个热源的协同散热问题已成为制约设备性能的关键瓶颈。该研究解决了“如何预测高热流电子设备的最小散热空间，同时确保VR设备中耦合热资源条件下芯片结温和排气温度的安全阈值”的科学问题。为此，建立了基于多物理场耦合的系统热管理框架。该模型包括石墨烯层的尺寸选择标准，窄通道中流动的一维稳态热分析以及MgAl框架的热扩散表达式。第三，设计了三嵌套优化体系结构。它利用内环路多物理场平衡、中环路通道参数调整和外环路风扇特性优化的协调反馈机制，在空间约束下动态匹配热性能。结果表明，典型VR模块所需的散热空间体积减少了27.2%。因此，本研究为虚拟现实热管理中固定性能约束下空间体积和热可行性的协同优化提供了理论工具。所提出的阈值触发机制也可扩展到其他紧凑型电子产品的热设计中，如智能可穿戴设备和微型机器视觉系统。

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引用次数: 0

Experimental evaluation of thermal and hydraulic performance in multi-layer microchannel heat sinks with various flow configurations 不同流态下多层微通道散热器热水力性能的实验评价

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-20 DOI: 10.1016/j.ijheatfluidflow.2026.110260

Hassan Abdelaty , Ahmed Omera , Mohamed Abdelgawad

Single-phase coolant flow in multi-layer microchannel heat sinks offers an effective alternative for removal of high heat fluxes generated by electronic devices and similar applications. This passive cooling technique enhances heat transfer without requiring additional external power, making it an attractive alternative to single-layer configurations. This study investigates the impact of number of layers and flow configurations on both thermal and hydraulic performances of microchannel heat sinks under a uniform heat flux up to 23.5 W/cm². Four layers and three flow configurations, parallel, counter, and crossflow were investigated. Experiments were conducted on CNC-machined, pure copper channels with square cross-sections (500 μm × 500 μm). The evaluation focused on key performance metrics, including pressure drop, surface temperature distribution, and thermal resistance. The results demonstrate significant improvements in thermal performance compared to single-layer heat sinks under identical testing conditions. Specifically, at the lowest flow rate, the thermal resistance is reduced by 9.7%, 21%, and 25.2% for the Double, Triple and Four-layer configurations, respectively, compared to the single layer one. In addition, Flow arrangement was found to influence performance, with increased flow in lower layers yielding enhanced temperature uniformity, reduced surface temperature, and lower thermal resistance. Furthermore, increasing number of layers has a significant influence on the pressure drop. Specifically, transitioning from Single-layer to Double-, Triple-, and Four-layer configurations results in pressure drop reductions of 41.2%, 55.3%, and 67.3%, respectively, at the maximum tested flow rate of 5.075 g/s.

多层微通道散热器中的单相冷却液流为去除电子设备和类似应用产生的高热流提供了有效的替代方案。这种被动冷却技术在不需要额外的外部电源的情况下增强了传热，使其成为单层配置的有吸引力的替代方案。在23.5 W/cm2的均匀热通量下，研究了层数和流动形态对微通道散热器热工性能和水力性能的影响。研究了平行流、逆流流和横流四层三种流态。实验采用cnc加工的方形截面纯铜通道（500 μm × 500 μm）。评估的重点是关键性能指标，包括压降、表面温度分布和热阻。结果表明，在相同的测试条件下，与单层散热器相比，其热性能有显著改善。具体而言，在最低流量下，与单层相比，双层、三层和四层结构的热阻分别降低了9.7%、21%和25.2%。此外，流动安排也会影响性能，下层流动增加，温度均匀性增强，表面温度降低，热阻降低。此外，层数的增加对压降有显著的影响。具体来说，当测试的最大流速为5.075 g/s时，从单层结构过渡到双层、三层和四层结构，压降分别降低了41.2%、55.3%和67.3%。

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引用次数: 0

RANS CFD applied to 2D canonical shock wave turbulent boundary layer interaction 二维正则激波湍流边界层相互作用的RANS CFD研究

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-02-02 DOI: 10.1016/j.ijheatfluidflow.2026.110263

Paul Canoville, Andrew Lewis

In high-speed flight, Shock Wave Turbulent Boundary Layer Interaction (SWTBLI) commonly occurs in a wide range of external and internal flow problems affecting aircraft, missiles, rockets, and other projectiles. The fundamental physics of SWTBLI are often best examined in canonical situations. A Reynolds Averaged Navier Stokes (RANS) Computational Fluid Dynamics (CFD) method prediction tool for simulating high-speed SWTBLI flow fields for 2D canonical configurations was enhanced in this research. RANS CFD method simulations are extensively used for engineering prediction of SWTBLI in high-speed flows. However, in the presence of strong shockwaves significant disagreement with experimental data is typically observed as all pertinent flow physics are not suitably captured by standard RANS simulations. Methods allowing for the effects of shock unsteadiness and variable turbulent Prandtl number PrT are integrated into the turbulence models of the RANS CFD method developed in this research to capture more of the pertinent flow physics associated at SWTBLI regions and so improve the calculations. Overall, results obtained from the modified turbulence models show a substantial improvement in prediction of key aerothermodynamic parameters for the strong SWTBLI flow test cases assessed as compared to results obtained using the standard turbulence closure models. For the oblique impinging shockwave configuration test case undertaken for example, the computed reattachment shock region peak surface heat flux error margin achieved against experiment by the standard models was demonstrated to be as high as 400% approximately. This error margin was reduced to as low as 15% by the modified models.

在高速飞行中，激波湍流边界层相互作用（SWTBLI）通常出现在影响飞机、导弹、火箭和其他射弹的各种内外流动问题中。SWTBLI的基本物理通常在规范的情况下得到最好的检验。研究了一种基于Reynolds平均Navier Stokes （RANS）计算流体动力学（CFD）方法的二维典型构型高速SWTBLI流场模拟预测工具。RANS CFD方法模拟广泛应用于高速流动中SWTBLI的工程预测。然而，在强激波存在的情况下，通常会观察到与实验数据的显著差异，因为所有相关的流动物理都不能被标准的RANS模拟适当地捕获。考虑激波非定常和可变湍流普朗特数PrT影响的方法被整合到本研究开发的RANS CFD方法的湍流模型中，以捕获更多与SWTBLI区域相关的相关流动物理，从而改进计算。总的来说，与使用标准湍流闭合模型获得的结果相比，改进的湍流模型获得的结果显示，在预测强SWTBLI流动测试用例的关键气动参数方面有了实质性的改进。以所进行的斜碰撞激波构型试验为例，通过标准模型计算得到的再附着激波区峰值表面热流密度与实验误差可达400%左右。修正后的模型将误差幅度降低到15%。

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引用次数: 0

Numerical simulation of turbulent concentric annular pipe flow using one-dimensional turbulence (ODT): Part 1: Momentum transfer 使用一维湍流（ODT）的同心环管湍流数值模拟：第1部分：动量传递

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-02-02 DOI: 10.1016/j.ijheatfluidflow.2026.110281

Pei-Yun Tsai, Marten Klein, Heiko Schmidt

Turbulent concentric coaxial (annular) pipe flow is numerically investigated using a stochastic one-dimensional turbulence (ODT) model as standalone tool. The dimensionally reduced ODT domain enables fully resolved numerical simulations of the flow across the radial gap between the cylindrical inner wall and the cylindrical outer wall. The model is calibrated with available reference data at low bulk Reynolds number

R e_{D_{h}} = 8900

for a wide (radius ratio

η = 0.1

) and a moderate (

η = 0.5

) gap. Making use of the model’s predictive capabilities, radius ratio and Reynolds number effects are investigated, reaching bulk Reynolds numbers as large as

R e_{D_{h}} = 1 0^{6}

. Despite the large

R e_{D_{h}}

values reached, spanwise wall-curvature effects remain sensible in the momentum boundary layer. The effects are more pronounced for larger wall curvature and to leading orders restricted to the convex cylindrical inner wall. Wall-curvature corrections to the law of the wall are obtained for both the viscous and Reynolds-stress dominated regions by fitting analytically derived expressions for the flow profile to the stochastic simulation data, demonstrating physical compatibility with Reynolds-averaged Navier–Stokes flow. Second-order and detailed fluctuation statistics demonstrate the permeating and nonlocal influence of spanwise wall curvature on the turbulent boundary layer. Surrogate model output in terms of conditional eddy event statistics reveals that the disparity between the near-inner and near-outer wall turbulence increases with Reynolds number for small radius ratios, suggesting that annular pipe flows require wall-curvature-aware wall models even at very large Reynolds numbers.

采用随机一维湍流（ODT）模型作为独立工具，对同心共轴（环空）管内的湍流进行了数值研究。尺寸减小的ODT域可以完全解析圆柱内壁和圆柱外壁之间径向间隙的流动数值模拟。在较宽（半径比η=0.1）和中等（η=0.5）间隙的低体积雷诺数ReDh=8900条件下，对模型进行了标定。利用模型的预测能力，研究了半径比和雷诺数效应，得到了大到ReDh=106的体积雷诺数。尽管达到了很大的ReDh值，但在动量边界层中，沿展向的壁面曲率效应仍然很明显。对于较大的壁曲率和仅限于凸圆柱形内壁的阶数，效果更为明显。通过将解析导出的流型表达式拟合到随机模拟数据中，得到了粘滞区和reynolds -应力主导区壁面曲率的修正，证明了与reynolds -平均Navier-Stokes流的物理相容性。二阶和详细的波动统计表明了跨向壁面曲率对湍流边界层的渗透和非局部影响。根据条件涡事件统计的替代模型输出表明，在小半径比下，近内壁和近外壁湍流度之间的差异随着雷诺数的增加而增加，这表明即使在非常大的雷诺数下，环空管道流动也需要壁面曲率感知的壁面模型。

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引用次数: 0

A novel air-assisted spray cooling approach using water–acetone mixtures for enhanced photovoltaic thermal management 一种新型的空气辅助喷雾冷却方法，使用水-丙酮混合物来增强光伏热管理

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-02-03 DOI: 10.1016/j.ijheatfluidflow.2026.110286

Adem Kilic, Kenan Yakut, Muhammet Harun Osta, Ahmet Numan Özakin, Hassen Ghaly

The increasing demand for sustainable energy has highlighted the need for advanced thermal management in photovoltaic (PV) systems. Excess heat accumulated on PV surfaces reduces carrier mobility and output voltage, thereby limiting energy conversion efficiency. Therefore, innovative cooling strategies that enhance heat transfer while maintaining economic feasibility are crucial for next-generation solar technologies. Various methods, including finned surfaces, phase-change materials, liquid films, and sprays, have been proposed for PV cooling, with air-assisted sprays standing out due to their high heat transfer and low energy demand. However, most existing air-assisted spray cooling studies have focused on pure water, ethanol, or nanofluids, while the thermal behavior of water–acetone binary mixtures remains insufficiently investigated. In this study, an air-assisted spray cooling system using water–acetone mixtures containing 0–45% acetone was experimentally and numerically examined. Four different nozzles were tested, and pressure-fed full-cone nozzles were found to produce smaller droplets and achieve higher heat transfer coefficients. Experiments were conducted under approximately 1000 W/m² irradiance, with a constant air flow rate of 4 m³/h and liquid flow rates between 150 and 800 mL/min. CFD results showed strong agreement with experimental data, with temperature deviations below 2 °C and time differences under 10%. Increasing the liquid flow rate and acetone content reduced the cooling time from 320 s (pure water) to 77 s. Owing to rapid evaporation, 400–600 mL/min flow rates and 15–30% acetone mixtures provided 9–22% faster cooling with only 190–380 USD additional annual operating cost.

对可持续能源日益增长的需求突出了对先进的光伏（PV）系统热管理的需求。在PV表面积累的多余热量降低了载流子迁移率和输出电压，从而限制了能量转换效率。因此，在保持经济可行性的同时加强传热的创新冷却策略对下一代太阳能技术至关重要。包括翅片表面、相变材料、液体薄膜和喷雾在内的各种方法已经被提出用于光伏冷却，其中空气辅助喷雾因其高传热和低能量需求而脱颖而出。然而，大多数现有的空气辅助喷雾冷却研究都集中在纯水、乙醇或纳米流体上，而水-丙酮二元混合物的热行为仍然没有得到充分的研究。在本研究中，使用含有0-45%丙酮的水-丙酮混合物对空气辅助喷雾冷却系统进行了实验和数值测试。测试了四种不同的喷嘴，发现加压式全锥喷嘴产生的液滴更小，传热系数更高。实验在约1000 W/m2的辐照度下进行，空气流速为4 m3/h，液体流速为150 ~ 800 mL/min。CFD结果与实验数据吻合较好，温度偏差小于2°C，时间差小于10%。增加液体流速和丙酮含量，使冷却时间从320 s（纯水）缩短到77 s。由于蒸发速度快，400-600 mL/min的流速和15-30%的丙酮混合物可使冷却速度加快9-22%，而每年的运营成本仅增加190-380美元。

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引用次数: 0

Research progress of film cooling on turbine blades with different profiles 不同叶型涡轮叶片气膜冷却研究进展

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-06 DOI: 10.1016/j.ijheatfluidflow.2026.110245

Jialin Liu , Guoqing Li , Chenfeng Wang , Xiaohui Bai , Yanfeng Zhang , Xingen Lu

Film cooling is a commonly used method to solve the high turbine inlet temperature for aero-engines. In recent decades, many studies on film cooling have been conducted based on various blade profiles. In order to summarize the film cooling performance of different blade profiles and provide help for subsequent film cooling design, an overview is conducted in this paper that highlights the effects of different blade profiles. Due to variations in secondary flow structures within the blade passages of different profiles, a comparative analysis is provided on the influence of secondary flow on film cooling performance. Through comparing film cooling performance of different profiles, local regions of high heat flux are formed in different parts of the blade surface under the influence of the passage vortex, leakage vortex, and inlet swirl. The size and location of these high heat flux regions are related to the profile geometry. Further research on film cooling could be conducted based on more complex bowed and twist blades, with precise and targeted design for high heat flux areas on the blade surface.

气膜冷却是解决航空发动机进气温度过高的常用方法。近几十年来，人们对不同叶片型线的气膜冷却进行了大量研究。为了总结不同叶型的气膜冷却性能，为后续的气膜冷却设计提供帮助，本文对不同叶型的效果进行了概述。由于不同叶型通道内二次流结构的差异，对比分析了二次流对气膜冷却性能的影响。通过对比不同叶型的气膜冷却性能，在通道涡、泄漏涡和进口涡的影响下，叶片表面不同部位形成了局部高热流密度区域。这些高热流区的大小和位置与剖面几何形状有关。进一步的气膜冷却研究可以基于更复杂的弯曲和扭曲叶片，对叶片表面的高热流密度区域进行精确和有针对性的设计。

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引用次数: 0

A new nonlinear dissipative boundary condition for internal incompressible flows 内部不可压缩流动的一个新的非线性耗散边界条件

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-21 DOI: 10.1016/j.ijheatfluidflow.2026.110274

Jacek Szumbarski , Jakub Gałecki

This paper presents a numerical methodology for modeling unsteady flows of viscous incompressible fluids within internal domains containing multiple inlet and outlet sections. A new formulation for dissipative boundary conditions, incorporating nonlinear terms, is introduced. The approach enables the imposition of time-dependent flow rates and/or section-averaged pressures at the domain boundaries. The solution technique relies on the instantaneous superposition of Stokes problems. Fluid motion unsteadiness is addressed by combining Backward Differentiation Formulae (BDF) schemes with Operator-Integration-Factor splitting (OIFS) and polynomial extrapolation to manage the model’s nonlinearities. Numerical simulation results, generated using a spectral element solver applied to a two-dimensional test case, are also detailed.

本文提出了粘性不可压缩流体在包含多个进出口截面的内域中非定常流动的数值模拟方法。引入了一种新的包含非线性项的耗散边界条件公式。该方法可以在区域边界处施加随时间变化的流速和/或截面平均压力。求解技术依赖于Stokes问题的瞬时叠加。通过将后向微分公式（BDF）与算子-积分-因子分裂（OIFS）和多项式外推相结合来处理模型的非线性，解决了流体运动的非定常问题。数值模拟结果，生成使用谱元求解器应用于二维测试用例，也详细。

引用次数: 0

Swirl air jets for high heat transfer in solar collectors 用于太阳能集热器高传热的旋流射流

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-01-22 DOI: 10.1016/j.ijheatfluidflow.2026.110270

Nagendra Kumar, Satyender Singh, Sanjay Kumar, Ranchan Chauhan

In the present experimental work, an array of swirl air jets impinging on hot absorber plate is investigated to improve the heat transfer in solar air heater. Swirling nozzles are designed and 3D printed to obtain different velocity and diameter of the air swirls. Various geometrical parameters related to swirling nozzles, such as height of nozzle

(30 m m \leq H \leq 50 m m)

and number of helix

(0 \leq ξ \leq 4)

for three different types of nozzles, i.e., smooth non-swirling (N₁), with twisted tap helix (N₂), and with twisted tap helix and central tube (N₃). The nozzle, N₃ presents a novel design that incorporates both smooth in the center and swirl (helix) configuration around to remove the heated zone that commonly left at the central region in swirl jet impingement. Thermal performance of solar air heater (SAH) for all three nozzles is analyzed and compared for the range of mass flow rate, i.e.,

0.01 k g / s \leq \dot{m} \leq 0.025 k g / s

. The results revealed high thermal performance for N₃ which is obtained as 93% and about 40% high in comparison to non-swirling nozzle, N1. Hence, using nozzle, N₃ about 9.5% enhancement is noticed in the thermal performance for the variation in H from 30 to 50 mm. The trends of thermohydraulic efficiency delineated the dominance of N₃ over other nozzle designs at lower mass flow rate and obtained as 68%, when H = 50 mm and

ξ

= 2. However, this investigation presents a novel insight in terms of different nozzles design and way forward in the improvement of thermal performance of SAH utilizing mixed swirls and air jets.

在本实验中，研究了一组旋流射流冲击吸热板以改善太阳能空气加热器的传热。设计并3D打印了旋转喷嘴，以获得不同速度和直径的空气漩涡。旋流喷嘴的各种几何参数，如喷嘴高度（30mm≤H≤50mm）和螺旋数（0≤ξ≤4），分别适用于三种不同类型的喷嘴，即光滑非旋流喷嘴（N1）、带旋锥螺旋喷嘴（N2）和带旋锥螺旋和中心管喷嘴（N3）。N3喷嘴采用了一种新颖的设计，它结合了中心光滑和周围的漩涡（螺旋）结构，以消除漩涡射流撞击中通常留在中心区域的加热区。在0.01kg/s≤≤0.025kg/s的质量流量范围内，对三种喷嘴的太阳能空气加热器（SAH）的热性能进行了分析比较。结果表明，N3的热工性能比非旋转喷嘴N1高93%，约40%。因此，使用喷嘴，当H从30到50 mm变化时，N3在热性能上提高了约9.5%。当H = 50 mm, ξ = 2时，热工效率的变化趋势表明，N3在较低质量流量下优于其他喷嘴设计，达到68%。然而，本研究在不同喷嘴设计方面提出了新的见解，并在利用混合漩涡和空气射流改善SAH的热性能方面取得了进展。

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引用次数: 0

Adaptive detached eddy simulation of transitional and massively separated flows around the S809 airfoil S809翼型周围过渡和大规模分离流动的自适应分离涡模拟

IF 2.6 3区工程技术 Q2 ENGINEERING, MECHANICAL

International Journal of Heat and Fluid Flow

Pub Date : 2026-04-01 Epub Date: 2026-02-10 DOI: 10.1016/j.ijheatfluidflow.2026.110304

Le He, Gaohua Li, Zifei Yin

The adaptive,

ℓ^{2} - ω

Delayed Detached Eddy Simulation model has the capability of adapting to local flow, and is proven to be capable of simulating orderly and bypass transition on flat plates (Yin et al., 2021). To answer the question of whether the adaptive,

ℓ^{2} - ω

model can predict the evolution of aerodynamic flow around a natural laminar airfoil at different angles of attack, a series of numerical simulations is performed for the S809 airfoil. A key prerequisite of the adaptive

ℓ^{2} - ω

model to predict transition is the resolution of precursor large-scale motions in the laminar boundary layer, which triggers the activation of modeled Reynolds stresses and thereby enables transition prediction. The present work explores the use of turbulence inflow generation and a low-dissipation, high-resolution numerical method to enable the simulation of transitional and separated flows around the S809 airfoil. The

ℓ^{2} - ω

model is capable of predicting distinct flow states occurring at various angles of attack. It not only captures laminar flow over a realistic airfoil shape, but also resolves spanwise variations in flow behavior.

自适应的，2−ω延迟分离涡模拟模型具有适应局部流动的能力，并被证明能够模拟平板上的有序和旁路过渡（Yin et al., 2021）。为了回答自适应的，2−ω模型是否可以预测在不同迎角的自然层流翼型周围的气动流动演变的问题，对S809翼型进行了一系列的数值模拟。自适应模型预测跃迁的一个关键前提是层流边界层中前驱体大尺度运动的分辨率，这触发了模型雷诺兹应力的激活，从而实现了跃迁预测。目前的工作探讨了使用湍流流入产生和低耗散，高分辨率的数值方法，使S809翼型周围的过渡和分离流动的模拟。2−ω模型能够预测不同迎角下不同的流动状态。它不仅捕获层流在一个现实的翼型形状，但也解决了流动行为的横向变化。

{"title":"Adaptive detached eddy simulation of transitional and massively separated flows around the S809 airfoil","authors":"Le He, Gaohua Li, Zifei Yin","doi":"10.1016/j.ijheatfluidflow.2026.110304","DOIUrl":"10.1016/j.ijheatfluidflow.2026.110304","url":null,"abstract":"<div><div>The adaptive, <span><math><mrow><msup><mrow><mi>ℓ</mi></mrow><mrow><mn>2</mn></mrow></msup><mo>−</mo><mi>ω</mi></mrow></math></span> Delayed Detached Eddy Simulation model has the capability of adapting to local flow, and is proven to be capable of simulating orderly and bypass transition on flat plates (<span><span>Yin et al., 2021</span></span>). To answer the question of whether the adaptive, <span><math><mrow><msup><mrow><mi>ℓ</mi></mrow><mrow><mn>2</mn></mrow></msup><mo>−</mo><mi>ω</mi></mrow></math></span> model can predict the evolution of aerodynamic flow around a natural laminar airfoil at different angles of attack, a series of numerical simulations is performed for the S809 airfoil. A key prerequisite of the adaptive <span><math><mrow><msup><mrow><mi>ℓ</mi></mrow><mrow><mn>2</mn></mrow></msup><mo>−</mo><mi>ω</mi></mrow></math></span> model to predict transition is the resolution of precursor large-scale motions in the laminar boundary layer, which triggers the activation of modeled Reynolds stresses and thereby enables transition prediction. The present work explores the use of turbulence inflow generation and a low-dissipation, high-resolution numerical method to enable the simulation of transitional and separated flows around the S809 airfoil. The <span><math><mrow><msup><mrow><mi>ℓ</mi></mrow><mrow><mn>2</mn></mrow></msup><mo>−</mo><mi>ω</mi></mrow></math></span> model is capable of predicting distinct flow states occurring at various angles of attack. It not only captures laminar flow over a realistic airfoil shape, but also resolves spanwise variations in flow behavior.</div></div>","PeriodicalId":335,"journal":{"name":"International Journal of Heat and Fluid Flow","volume":"119 ","pages":"Article 110304"},"PeriodicalIF":2.6,"publicationDate":"2026-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"146170015","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

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