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Linear-Stability-Based Transition Modeling for aerodynamic flow simulations with a Near-Wall Reynolds-Stress Model

AIAA JOURNAL 2012年第2期50卷 416-428页

作者： Probst, A. Radespiel, R. Rist, U. Tech Univ Carolo Wilhelmina Braunschweig Inst Fluid Mech D-38106 Braunschweig Germany Univ Stuttgart Inst Aerodynam & Gas Dynam D-70550 Stuttgart Germany

An extended e(N)-based modeling approach. for Tollmien-Schlichting-type transition in aerodynamic flow simulations with the low-Re epsilon(h)-Reynolds-stress model is presented. Instead of simply activating the turbulence production terms at the transition location (point-transition approach), the method incorporates the otherwise neglected Reynolds-stress contributions by the fluctuations of the Tollmien-Schlichting waves and provides them as local input for the turbulence model at the transition point. The shapes of the Reynolds-stress profiles are derived from linear stability analysis within the e(N) method, whereas their absolute magnitudes are calibrated with the aid of direct numerical simulation data of a transitional boundary layer with adverse-pressure gradient. The dissipation-rate input is adjusted to theoretically match the amplification rate of the fluctuations but requires a correction to account for the low-Re damping in the epsilon(h)-Reynolds-stress model. The paper describes the general modeling ideas and the implementation in the flow solver. Aspects of the numerical discretization and a verification for three-dimensional flows are addressed as well. Besides a basic validation for the adverse-pressure-gradient boundary layer, simulations of the SD7003 airfoil flow comprising a laminar separation bubble are presented, which yield very good agreement with measurements. Results of a transitional flat-plate flow are, however, impaired by the lack of intermittency modeling. Finally, the method is applied to a flowthrough nacelle near stall conditions in order to prove its ability to compute consistent transitional behavior in complex three-dimensional flows.

关键词： aerodynamic Coefficients Reynolds Averaged Navier Stokes aerodynamic flow simulations Laminar Turbulent Transition Aircraft Configurations Turbulence Models Nonequilibrium flows Skin Friction Coefficient Stress Distribution Reynolds Stress Equation

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Unified LSPG Model Reduction Framework and Assessment for Hypersonic Computational Fluid Dynamics

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AIAA JOURNAL 2025年第1期63卷 72-90页

作者： Chmiel, Matthew R. Barnett, Joshua Farhat, Charbel Stanford Univ Dept Aeronaut & Astronaut Durand BldgRoom 224 Stanford CA 94305 USA Stanford Univ Dept Mech Engn Durand BldgRoom 224 Stanford CA 94305 USA Stanford Univ Aeronaut & Astronaut Durand BldgRoom 257 Stanford CA 94305 USA

A unified least-squares Petrov-Galerkin (LSPG) framework for projection-based model order reduction featuring three different approximation manifolds [affine manifold, quadratic manifold, and nonlinear manifold built using a deep artificial neural network (ANN)] is presented. Its performance was assessed for a variable-speed version of the double-cone hypersonic benchmark problem. First, a high-dimensional viscous computational fluid dynamics model (HDM) was constructed, verified, and validated. The dimensionality of the HDM was then reduced using LSPG, each of the aforementioned approximation manifolds, and a global right reduced-order basis trained in the range 8 <= M infinity <= 13. Each resulting global projection-based reduced-order model (PROM) was hyper-reduced and transformed into a hyper-reduced PROM (HPROM). The accuracy of each constructed HPROM was assessed for various quantities of interest and contrasted with that of snapshot interpolation. For this purpose, three different error measures were considered and discussed in the context of shock-dominated problems. Wall-clock and CPU time speedup factors are reported. Overall, it was shown that using a relatively small set of training data, all constructed LSPG HPROMs were nonlinearly stable, real-time capable, and highly predictive. The LSPG HPROM constructed using a nonlinear approximation manifold and an ANN was the most computationally efficient.

关键词： Computational Fluid Dynamics Artificial Neural Network Reduced Order Modelling Boundary Layers Reynolds Averaged Navier Stokes Detached Shock Reduced Order Model aerodynamic flow simulations Hypersonic aerodynamics Applied aerodynamics

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TURBULENT TRANSONIC AIRFOIL flow SIMULATION USING A PRESSURE-BASED ALGORITHM

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AIAA JOURNAL 1995年第1期33卷 42-47页

作者： ZHOU, G DAVIDSON, L OLSSON, E Chalmers University of Technology S-412 96 Gothenburg Sweden

There are few successful computational reports for transonic airfoil now worked out with the pressure-based method. In this study, an advanced approach based on a pressure correction scheme is developed to solve the Reynolds-averaged Navier-Stokes equations for turbulent transonic now around the airfoil RAE 2822. An implicit numerical dissipation model is adopted to create a dissipation mechanism based on pressure gradients to damp the destabilizing numerical effects, without smearing the physical discontinuity at shocks. The standard k-epsilon turbulence closure with a near-wall one-equation model is used. The computational results are compared with experimental data. Several discretization schemes such as the second-order upwind, hybrid, and MUSCL schemes for convection terms are investigated. The computational results show that the proposed pressure-based method has a resolution comparable to, or better than, the traditional time-marching methods.

关键词： Freestream Mach Number RAE 2822 Reynolds Averaged Navier Stokes Two Dimensional flow Convection Angle of Attack aerodynamic flow simulations Mass Flux Kinetic Energy Eddy Viscosity

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Re-engineering the design process through computation

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JOURNAL OF AIRCRAFT 1999年第1期36卷 36-50页

作者： Jameson, A Princeton Univ Princeton NJ 08544 USA

Examines ways to exploit computational simulation more effectively in the overall design process with the primary focus on aerodynamic design. Phases of the design process; Main requirements for effective computationa... 详细信息

关键词： aerodynamic Shape Optimization aerodynamic flow simulations Wing Body Combination Reynolds Averaged Navier Stokes Wind Tunnel Models aerodynamic Efficiency Aircraft Configurations Wide Body Transport Aircraft Euler Equations McDonnell Douglas

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Multifidelity Approach to Sensitivity Estimation in Large-Eddy Simulation

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AIAA JOURNAL 2023年第8期61卷 3485-3495页

作者： Arias-Ramirez, Walter Oberoi, Nikhil Larsson, Johan Univ Maryland Dept Mech Engn College Pk MD 20742 USA

A novel approach to compute affordable approximate sensitivities in a large-eddy simulation (LES) is proposed and assessed. The approach is based on solving a Reynolds-averaged Navier-Stokes (RANS) problem that has been linearized around the mean LES solution, with closure modeling required for the linearized changes in turbulent Reynolds stresses. In the present study, the closure modeling is based on a linearized algebraic turbulence model. The method is assessed for the flow over a NACA0012 airfoil at a fixed angle of attack, with the Reynolds number as the variable parameter. The results show that, provided an accurate linearized closure model, the method predicts the correct sensitivity of the skin friction coefficient and the mean velocity field at the cost of a linearized RANS, which provides an important proof-of-concept for this approach. The linearized algebraic turbulence model with standard model coefficients produces a reasonably accurate sensitivity, but the results also suggest that accuracy could be gained from recalibrating the model coefficients for this new use of the model.

关键词： Computational Fluid Dynamics Airfoil Skin Friction Coefficient Turbulence Models Sensitivity Analysis Large Eddy Simulation aerodynamic flow simulations Statistical Analysis aerodynamic Drag Reynolds Averaged Navier Stokes

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Introduction to the Selected Papers from NATO AVT-338 Specialists Meeting on Advanced Wind Tunnel Boundary Simulation II Virtual Collection

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JOURNAL OF AIRCRAFT 2024年第1期61卷 5-6页

作者： Huber, Kerstin C. Smith, Marilyn J. Lee-Rausch, Elizabeth M. German Aerosp Ctr D-12489 Berlin Germany Georgia Inst Technol Atlanta GA USA NASA Langley Res Ctr Hampton VA USA

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New advanced k-w turbulence model for high-lift aerodynamics

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AIAA JOURNAL 2005年第9期43卷 1857-1869页

作者： Hellsten, A Helsinki Univ Technol Lab Aerodynam FIN-02015 Helsinki Finland

The development and preliminary validation of a new k-omega turbulence model based on explicit algebraic Reynolds-stress modeling are presented. This new k-omega model is especially designed for the requirements typical in high-lift aerodynamics. Attention is especially paid to the model behavior at the turbulent/laminar edges, to the model sensitivity to pressure gradients, and to the calibration of the model coefficients for appropriate flow phenomena. The model development is based on both analytical studies and numerical experimenting. The developed;model is assessed and validated for a set of realistic flow problems including high-lift airfoil flows.

关键词： aerodynamic Force Coefficients Turbulence Models Adverse Pressure Gradient Kinematic Viscosity Boundary Layer Equations Nonequilibrium flows Lift Coefficient Stress Distribution aerodynamic flow simulations Diffusion Coefficient

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Adjoint-based Anisotropic Mesh Adaptation for a Stabilized Finite-Element flow Solver

Adjoint-based Anisotropic Mesh Adaptation for a Stabilized F...

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AIAA Aviation Forum and Exposition

作者： Balan, Aravind Park, Michael A. Anderson, W. Kyle NASA Langley Res Ctr Hampton VA 23681 USA NASA Langley Res Ctr Computat AeroSci Branch Hampton VA 23681 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

An adjoint solver is implemented in the FUN3D stabilized finite-element flow solver. The adjoint solution is used to generate anisotropic, adapted meshes to control error in scalar output functionals, such as lift or drag coefficient. The inviscid and turbulent adjoints are verified with a finite-difference derivative approximation and can be used in design optimization in addition to mesh adaptation. The adjoint capability represents an extension of previous research using the FUN3D stabilized finite-element capability with metric-based mesh adaptation and interpolation-based error estimates to generate highly anisotropic adapted meshes for turbulent flows. In the present work, a metric-based approach is again utilized, where the adjoint and the primal solutions both contribute to the generation of a metric tensor field that is subsequently used to produce the required anisotropic mesh for each adaptation cycle. Adaptive results are then shown for an inviscid supersonic flow over a diamond airfoil, inviscid transonic flow over the ONERA M6 wing, and viscous laminar flow over the NACA 0012 airfoil, all using drag force as the output functional. Adjoint-based adaptation is compared with a multiscale solution-based approach that controls the L-p norm of Mach number interpolation error to demonstrate the effectiveness and e fficiency of the adjoint-based adaptive mesh technology.

关键词： Supersonic flow Drag Coefficient NACA 0012 FUN3D Angle of Attack aerodynamic flow simulations Unstructured Grid Continuity Equation Variational Multiscale Method Application Programming Interface

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