Computers & Fluids最新文献

Isobaric steady-state preserving adaptive surface reconstruction schemes for the two-dimensional Ripa system on triangles

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-13 DOI: 10.1016/j.compfluid.2025.106664

Jian Dong, Xu Qian, Zige Wei

引用次数: 0

Large airfoil models 大型翼型模型

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-10 DOI: 10.1016/j.compfluid.2025.106662

Howon Lee, Aanchal Save, Pranay Seshadri, Juergen Rauleder

{"title":"Large airfoil models","authors":"Howon Lee, Aanchal Save, Pranay Seshadri, Juergen Rauleder","doi":"10.1016/j.compfluid.2025.106662","DOIUrl":"10.1016/j.compfluid.2025.106662","url":null,"abstract":"<div><div>The development of a Large Airfoil Model (LAM), a transformative approach for answering technical questions on airfoil aerodynamics, requires a vast dataset and a model to leverage it. To build this foundation, a novel probabilistic machine learning approach, A Deep Airfoil Prediction Tool (ADAPT), has been developed. ADAPT makes uncertainty-aware predictions of airfoil pressure coefficient (<span><math><msub><mrow><mi>C</mi></mrow><mrow><mi>p</mi></mrow></msub></math></span>) distributions by harnessing experimental data and incorporating measurement uncertainties. By employing deep kernel learning, performing Gaussian Process Regression in a ten-dimensional latent space learned by a neural network, ADAPT effectively handles unstructured experimental datasets. In tandem, Airfoil Surface Pressure Information Repository of Experiments (ASPIRE), the first large-scale, open-source repository of airfoil experimental data, has been developed. ASPIRE integrates century-old historical data with modern reports, forming an unparalleled resource of real-world pressure measurements. This addresses a critical gap left by prior repositories, which relied primarily on numerical simulations. Demonstrative results for three airfoils show that ADAPT accurately predicts <span><math><msub><mrow><mi>C</mi></mrow><mrow><mi>p</mi></mrow></msub></math></span> distributions and aerodynamic coefficients across varied flow conditions, achieving a mean absolute error in enclosed area (<span><math><msub><mrow><mtext>MAE</mtext></mrow><mrow><mtext>enclosed</mtext></mrow></msub></math></span>) of 0.029. ASPIRE and ADAPT lay the foundation for an interactive airfoil analysis tool driven by a large language model, enabling users to perform design tasks based on natural language questions rather than explicit technical input.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"298 ","pages":"Article 106662"},"PeriodicalIF":2.5,"publicationDate":"2025-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144069420","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}

引用次数: 0

Neural operators learn the local physics of magnetohydrodynamics 神经算子学习磁流体力学的局部物理

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-09 DOI: 10.1016/j.compfluid.2025.106661

Taeyoung Kim , Youngsoo Ha , Myungjoo Kang

{"title":"Neural operators learn the local physics of magnetohydrodynamics","authors":"Taeyoung Kim , Youngsoo Ha , Myungjoo Kang","doi":"10.1016/j.compfluid.2025.106661","DOIUrl":"10.1016/j.compfluid.2025.106661","url":null,"abstract":"<div><div>Magnetohydrodynamics (MHD) plays a pivotal role in describing the dynamics of plasma and conductive fluids, essential for understanding phenomena such as the structure and evolution of stars and galaxies, and in nuclear fusion for plasma motion through ideal MHD equations. Solving these hyperbolic PDEs requires sophisticated numerical methods, presenting computational challenges due to complex structures and high costs. Recent advances introduce neural operators like the Fourier Neural Operator (FNO) as surrogate models for traditional numerical analysis. This study proposes a modified Flux Neural Operator (Flux NO) model to approximate the numerical flux of ideal MHD, offering a novel approach with enhanced generalization capabilities and significant computational efficiency. Our methodology adapts the Flux NO to process each physical quantity individually and incorporates loss functions ensuring total variation diminishing (TVD) property and divergence freeness for numerical stability. The proposed method achieves superior generalization beyond sampled distributions compared to existing neural operators and demonstrates computation speeds 25 times faster than the reference numerical scheme.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"297 ","pages":"Article 106661"},"PeriodicalIF":2.5,"publicationDate":"2025-05-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936340","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}

引用次数: 0

A distributed element roughness model for generalized surface morphologies 广义表面形貌的分布单元粗糙度模型

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-08 DOI: 10.1016/j.compfluid.2025.106651

Samuel Altland , Vishal Wadhai , Shyam Nair , Xiang Yang , Robert Kunz , Stephen McClain

{"title":"A distributed element roughness model for generalized surface morphologies","authors":"Samuel Altland , Vishal Wadhai , Shyam Nair , Xiang Yang , Robert Kunz , Stephen McClain","doi":"10.1016/j.compfluid.2025.106651","DOIUrl":"10.1016/j.compfluid.2025.106651","url":null,"abstract":"<div><div>Flow over rough surfaces has been studied and modeled for many decades, due to its important role in turbulent boundary layer evolution and attendant drag and heat transfer amplification. While explicit resolution of deterministic and random roughness morphologies is often feasible given a geometry specification (i.e., CAD and/or optical scanning), CFD modeling of these roughness resolved configurations can be cost prohibitive in a design environment for DNS, LES and even sublayer resolved RANS. For this reason, surface parameterization based modeling is widely used to reduce computational cost. However, this approach suffers from many deficiencies, including ambiguity in determining the appropriate representative roughness length scale, and limitations associated with correctly predicting friction and heat transfer simultaneously. An alternative to surface parametrization is volumetric parameterization. Distributed Element Roughness Modeling (DERM) is an example of such a method. In this work, a DERM model based on the Double-Averaged Navier–Stokes (DANS) equations is developed. This formulation represents a <em>complete</em> treatment in that the three unclosed momentum transport processes that arise are each modeled; the roughness induced drag, the dispersive stress and the spatially averaged Reynolds stress. The models presented here are formulated based on physical and dimensional arguments, and are calibrated and validated using roughness resolved DNS, and neural network based machine learning. Three classes of surface topology are considered. These include cube arrays of varying packing density, sinusoidal roughness patterns of varying wavelengths, and random distributions associated with real additively manufactured surfaces. While DERM models are typically calibrated to specific deterministic roughness shape families, the results shown here demonstrate the wider range of applicability for the present, more generalized formulation.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"298 ","pages":"Article 106651"},"PeriodicalIF":2.5,"publicationDate":"2025-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144084135","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}

引用次数: 0

Energy preserving high order mimetic methods for Hamiltonian equations 哈密顿方程的保能高阶模拟方法

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-08 DOI: 10.1016/j.compfluid.2025.106642

Anand Srinivasan, José E. Castillo

{"title":"Energy preserving high order mimetic methods for Hamiltonian equations","authors":"Anand Srinivasan, José E. Castillo","doi":"10.1016/j.compfluid.2025.106642","DOIUrl":"10.1016/j.compfluid.2025.106642","url":null,"abstract":"<div><div>Hamiltonian equations possess a Hamiltonian function that governs the conserved physical property for the system. Obtaining a discretization scheme that satisfies the intrinsic geometric properties of its continuum problem is often a challenge. Spatial schemes that discretely mimic a conservation law are known to result in accurate discretizations of partial differential equations. The mimetic methods considered in this paper for spatial discretization are based on the work of Castillo & co-authors. These methods produce high order mimetic operators which, by construction, result in a discrete equivalent to a conservation law. These operators work on staggered spatial grids and produce even orders of accuracy at the boundaries and interiors, while avoiding the use of ghost nodes. The high order mimetic operators <span><math><mi>D</mi></math></span> and <span><math><mi>G</mi></math></span> are discrete approximations of their continuum counterpart vector calculus identities of divergence and gradient. The resulting discretizations are therefore said to mimic the underlying physics. The preservation of the spatio-temporal energy evolution requires a corresponding time integration scheme that is structure preserving, such as the staggered leapfrog scheme. The traditional leapfrog scheme, however, is limited to second order accuracy. In this work, we study the high order composition temporal methods with the mimetic operators to investigate the energy preserving aspects of Hamiltonian systems. Fourth and sixth order spatio-temporal energy preserving schemes are presented for both linear and non-linear Hamiltonian systems. The novelty of this work includes the validation of a sixth order mimetic energy preserving numerical scheme for non-linear Hamiltonian systems. Numerical examples that illustrate our findings are also presented in this work.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"297 ","pages":"Article 106642"},"PeriodicalIF":2.5,"publicationDate":"2025-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143936341","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}

引用次数: 0

A CVFEM-based coupled flow solver combined with a fully implicit Discontinuous Galerkin method for non-conformal grid interfaces 基于cvfem的非保形网格界面耦合流动求解与全隐式间断伽辽金法

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-08 DOI: 10.1016/j.compfluid.2025.106624

Luca Mangani , Mhamad Mahdi Alloush , Fadl Moukalled

引用次数: 0

High fidelity computational aerodynamics of micro unmanned aerial vehicle propeller 微型无人机螺旋桨的高保真计算空气动力学

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-07 DOI: 10.1016/j.compfluid.2025.106649

Alexis Dorange, Christophe Benoit, Eric Garnier

{"title":"High fidelity computational aerodynamics of micro unmanned aerial vehicle propeller","authors":"Alexis Dorange, Christophe Benoit, Eric Garnier","doi":"10.1016/j.compfluid.2025.106649","DOIUrl":"10.1016/j.compfluid.2025.106649","url":null,"abstract":"<div><div>The current surge in interest surrounding small unmanned aerial vehicles can be attributed to their extensive range of applications. This growing interest is not accompanied by a corresponding increase in knowledge regarding their aeroacoustic performance and behavior. Studies concentrate on commercial geometries, with low-fidelity models being employed as they are deemed sufficient for the acquisition of the requisite quantities for flight mechanics. This paper aims at providing a detailed description of a drone propeller aeroacoustic performance using a high level of modeling. This propeller is computed with a Large Eddy Simulation turbulence model and with two distinct mesh resolutions. The aeroacoustic performance of the propeller is evaluated for both configurations and compared to quantify the losses due to the reduction in mesh resolution, with the aim of limiting the computational cost. It is observed that the grid resolution does not affect the computation of the integral force. Furthermore, the overall flow topology remains qualitatively similar, despite some localized quantitative differences. Notably, the size of the separated region varies, and discrepancies in the computed acoustic waves and energy levels are observed between the simulations.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"297 ","pages":"Article 106649"},"PeriodicalIF":2.5,"publicationDate":"2025-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143922499","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}

引用次数: 0

Discontinuous Galerkin spectral element method with hybrid sub-element order reduction for shock-capturing with Navier–Stokes equations

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-05 DOI: 10.1016/j.compfluid.2025.106650

Fengrui Zhang, Yulia T. Peet

引用次数: 0

Embedded LES of a turbulent thermal boundary layer over ice roughness 冰层粗糙度上湍流热边界层的嵌入LES

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-05 DOI: 10.1016/j.compfluid.2025.106652

Denis Sotomayor-Zakharov , Riccardo Gaudioso , Mariachiara Gallia

{"title":"Embedded LES of a turbulent thermal boundary layer over ice roughness","authors":"Denis Sotomayor-Zakharov , Riccardo Gaudioso , Mariachiara Gallia","doi":"10.1016/j.compfluid.2025.106652","DOIUrl":"10.1016/j.compfluid.2025.106652","url":null,"abstract":"<div><div>The numerical prediction of ice accretion via icing codes relies on the proper estimation of the heat transfer coefficient on rough ice geometries. To understand the heat transfer physics at play, direct numerical simulations (DNS) on rough surfaces can be performed, although this results in a very expensive option if geometries obtained from different icing conditions want to be analyzed. Large eddy simulation (LES) presents itself as a less expensive option to perform such studies, giving insight into the physics of turbulence, as well as opening the possibility for calibration of roughness models. The present study verifies and validates a setup to perform embedded LES (ELES) of a zero pressure gradient incompressible flow over a flat plate with ice roughness heated to a constant wall temperature. An experimental database is used, which provides the geometries of rough plates obtained from unwrapped scans of ice shapes generated on a NACA0012 airfoil. The low-speed flow over the flat plate presents a <span><math><mrow><mi>R</mi><msub><mrow><mi>e</mi></mrow><mrow><mi>L</mi></mrow></msub><mo>=</mo><mn>3</mn><mo>.</mo><mn>85</mn><mi>⋅</mi><mn>1</mn><msup><mrow><mn>0</mn></mrow><mrow><mn>5</mn></mrow></msup></mrow></math></span> and <span><math><mrow><mi>P</mi><mi>r</mi><mo>=</mo><mn>0</mn><mo>.</mo><mn>729</mn></mrow></math></span>. The verification is carried out by analyzing the effects of the mesh resolution and the domain span on wall properties such as the skin friction coefficient and Stanton number. Additionally, an analysis of turbulence-related flow statistics is performed to guarantee the proper development of turbulence. The validation shows good agreement between ELES results and experimental data, especially for the Stanton number distributions, showcasing that this setup can be used for the study of heat transfer on ice roughness.</div></div>","PeriodicalId":287,"journal":{"name":"Computers & Fluids","volume":"297 ","pages":"Article 106652"},"PeriodicalIF":2.5,"publicationDate":"2025-05-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143917772","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}

引用次数: 0

Extension to non-uniform meshes of a high order computationally explicit kinetic scheme for hyperbolic conservation laws

IF 2.5 3区工程技术

Computers & Fluids Pub Date : 2025-05-03 DOI: 10.1016/j.compfluid.2025.106648

Rémi Abgrall , Stéphane Del Pino , Axelle Drouard , Emmanuel Labourasse

引用次数: 0