Grid Quality and Resolution Issues from the Drag Prediction Workshop Series

Mavriplis, Dimitri J.; Vassberg, John C.; Tinoco, Edward N.; Mani, Mori; Brodersen, Olaf; Eisfeld, Bernhard; Wahls, Richard A.; Morrison, Joseph H.; Zickuhr, Tom; Levy, David W.; Murayama, Mitsuhiro

doi:10.2514/1.39201

Cited by 62 publications

(6 citation statements)

References 40 publications

(40 reference statements)

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“…The DPW-III was heavily documented with summary papers [24,25], a statistical analysis paper [26], participant papers [27][28][29][30], and a special section of the AIAA Journal of Aircraft, edited by Vassberg [31][32][33][34][35][36]. After three workshops, the organizing committee recognized that a recurring theme of the workshop series was related to grid quality and resolution-see [37].…”

mentioning

confidence: 99%

Summary Data from the Sixth AIAA CFD Drag Prediction Workshop: CRM Cases

Tinoco¹,

Brodersen²,

Keye³

et al. 2018

Journal of Aircraft

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111

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Results from the Sixth AIAA CFD Drag Prediction Workshop Cases 2 to 5 are presented. These cases focused on force/moment and pressure predictions for the NASA Common Research Model wing-body and wing-body-nacellepylon configurations. The Common Research Model geometry differed from previous workshops in that it was deformed to the appropriate static aeroelastic twist and deflection at each specified angle of attack. The grid refinement study and nacelle-pylon drag increment prediction (Case 2) used a common set of overset and unstructured grids, as well as user-created multiblock structured, unstructured, and Cartesian-based grids. Solutions were requested for both the wing-body and wing-body-nacelle-pylon at a fixed Mach number and lift coefficient. The wing-body static aeroelastic/buffet study (Case 3) specified an angle-of-attack sweep at finely spaced intervals through the zone where wing separation was expected to begin. The optional Case 4 requested grid adaption solutions of the wing-body at a specified flight condition. Optional Case 5 requested coupled aerostructural wing-body solutions. Results from this workshop highlight the progress made since the last workshop, and the continuing need for computational fluid dynamics (CFD) improvement, particularly for conditions with significant flow separation. These comparisons also suggest the need for improved experimental diagnostics to guide future CFD development.

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mentioning

confidence: 99%

Summary Data from the Sixth AIAA CFD Drag Prediction Workshop: CRM Cases

Tinoco¹,

Brodersen²,

Keye³

et al. 2018

Journal of Aircraft

Self Cite

111

View full text Add to dashboard Cite

show abstract

“…The American Institute of Aeronautics and Astronautics (AIAA) has been an inspiration, with its Drag Prediction Workshops (DPW) [6] propelling advancements in Computational Fluid Dynamics (CFD) predictions. These workshops have established benchmark geometries, enabling a side-by-side comparison of CFD methodologies with empirical results.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the powered take-off configuration of civil transport using an improved thrust-drag bookkeeping method

Cui,

Zhang,

Wang

et al. 2024

J. Phys.: Conf. Ser.

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This paper offers a detailed examination of the powered nacelle’s effect on take-off configuration of a civil transport. Using computational fluid dynamics (CFD) techniques, we analyzed two specific geometries from the Propulsion Aerodynamics Workshop and High-lift Prediction Workshop, comparing our results with existing experimental data. We incorporated configurations of both the Through-flow Nacelle (TFN) and Power Nacelle (PN) for a comprehensive comparison. Our approach significantly refined the prevailing thrust-drag accounting method. Employing surface flow visualizations and spatial particle trajectories, we highlighted the powered nacelle’s influence on the aircraft flow field. Simulations show that the engine exhaust’s flow acceleration boosts lift and reduces flow separation at high angles of attack. However, power intervention notably increases the overall drag. Specifically, at a 14° angle of attack, power effects raise the drag coefficient of the take-off configuration by 275 counts, resulting in a 0.76 decrease in the lift-to-drag ratio.

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“…The use of Reynolds-averaged Navier-Stokes (RANS) with a turbulence model has become a critical tool for the design of aerospace vehicles. However, the issues that affect the grid convergence of three dimensional (3D) configurations are not completely understood, as documented in the AIAA Drag Prediction Workshop series [1][2][3]. To identify and address the issues preventing grid convergence, a series of special sessions has been organized for the Evaluation of RANS Solvers on Benchmark Aerodynamic Flows [4].…”

Section: Introductionmentioning

confidence: 99%

Unstructured Grid Adaptation and Solver Technology for Turbulent Flows

Park

Barral

Ibanez

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Unstructured grid adaptation is a tool to control Computational Fluid Dynamics (CFD) discretization error. However, adaptive grid techniques have made limited impact on production analysis workflows where the control of discretization error is critical to obtaining reliable simulation results. Issues that prevent the use of adaptive grid methods are identified by applying unstructured grid adaptation methods to a series of benchmark cases. Once identified, these challenges to existing adaptive workflows can be addressed. Unstructured grid adaptation is evaluated for test cases described on the Turbulence Modeling Resource (TMR) web site, which documents uniform grid refinement of multiple schemes. The cases are turbulent flow over a Hemisphere Cylinder and an ONERA M6 Wing. Adaptive grid force and moment trajectories are shown for three integrated grid adaptation processes with Mach interpolation control and output error based metrics. The integrated grid adaptation process with a finite element (FE) discretization produced results consistent with uniform grid refinement of fixed grids. The integrated grid adaptation processes with finite volume schemes were slower to converge to the reference solution than the FE method. Metric conformity is documented on grid/metric snapshots for five grid adaptation mechanics implementations. These tools produce anisotropic boundary conforming grids requested by the adaptation process.

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Grid Quality and Resolution Issues from the Drag Prediction Workshop Series

Cited by 62 publications

References 40 publications

Summary Data from the Sixth AIAA CFD Drag Prediction Workshop: CRM Cases

Summary Data from the Sixth AIAA CFD Drag Prediction Workshop: CRM Cases

Numerical investigation of the powered take-off configuration of civil transport using an improved thrust-drag bookkeeping method

Unstructured Grid Adaptation and Solver Technology for Turbulent Flows

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