Navier-Stokes computations and experimental comparisons for multielement airfoil configurations

Anderson, W. Kyle; Bonhaus, Daryl L.; McGhee, Robert; Walker, Betty S.

doi:10.2514/3.46871

Cited by 43 publications

(23 citation statements)

References 19 publications

(13 reference statements)

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“…Figure 10 shows the plot of Coefficient of Pressure versus x/c at 16 o angle of attack, comparing results of computational and experimental data of the airfoil MDA30P30N [5]. It can be seen that computed pressure distribution result is in good agreement with the experimental measurements.…”

Section: Numerical Validationsupporting

confidence: 66%

“…It was concluded that the S1223RTL airfoil had the most suitable design for the specified boundary conditions and the Mach numbers from 0.10 to 0.30. W. Kyle Anderson et al [5], did an experiment on a twodimensional unstructured Navier-Stokes code utilized for computing the flow around multi-element airfoil configurations. In the experiment, comparisons were shown for a landing configuration with an advanced-technology flap.…”

Section: Literature Surveymentioning

confidence: 99%

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Comparative Numerical Analysis of High Lift Airfoils and Effect of Mach Numbers Using CFD

Kumar¹,

Yadav²,

Mandloi³

et al. 2017

IJRET

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Section: Numerical Validationsupporting

confidence: 66%

Section: Literature Surveymentioning

confidence: 99%

Comparative Numerical Analysis of High Lift Airfoils and Effect of Mach Numbers Using CFD

Kumar¹,

Yadav²,

Mandloi³

et al. 2017

IJRET

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“…Similarly, in addition to their direct effect on friction drag, inaccuracies in computed skin friction can alter the prediction of downstream separation locations, which results in a much more profound effect on overall drag prediction. An example of this behavior was originally given Anderson et al, 29 and reproduced in reference, 30 where the effects of inadequate boundarylayer resolution were found to produce premature separation on a two-dimensional high-lift configuration. Examination of individual workshop results has shown that grid resolution requirements for drag prediction involving regions of separated flow are much more demanding and less well understood than for cases where the flow is fully attached.…”

Section: A Grid Resolutionmentioning

confidence: 99%

Grid Quality and Resolution Issues from the Drag Prediction Workshop Series

Mavriplis

Vassberg

Tinoco

et al. 2009

Journal of Aircraft

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The drag prediction workshop series (DPW), held over the last six years, and sponsored by the AIAA Applied Aerodynamics Committee, has been extremely useful in providing an assessment of the state-of-the-art in computationally based aerodynamic drag prediction. An emerging consensus from the three workshop series has been the identification of spatial discretization errors as a dominant error source in absolute as well as incremental drag prediction. This paper provides an overview of the collective experience from the workshop series regarding the effect of grid-related issues on overall drag prediction accuracy. Examples based on workshop results are used to illustrate the effect of grid resolution and grid quality on drag prediction, and grid convergence behavior is examined in detail. For fully attached flows, various accurate and successful workshop results are demonstrated, while anomalous behavior is identified for a number of cases involving substantial regions of separated flow. Based on collective workshop experiences, recommendations for improvements in mesh generation technology which have the potential to impact the state-of-the-art of aerodynamic drag prediction are given.

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“…Flow phenomena around high-lift devices are considered challenging for numerical methods and turbulence model discretisation; deployed slat and flap at high angles of attack in combination with low speed, potential unsteady flow regime, flow separation, laminar/turbulent transition, interaction of aerofoil/wing has been previously studied experimentally by Spaid [69]a n db yR u m s e ye ta l [ 70], where 3D effects are analysed including CFD simulations, further CFD work is presented in the following papers [71][72][73][74].…”

Section: Mda 30p-30nmentioning

confidence: 99%

Assessment of high-order finite volume methods on unstructured meshes for RANS solutions of aeronautical configurations

2017

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This version is available at https://strathprints.strath.ac.uk/59947/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output. Assessment of High-Order Finite Volume Methods on Unstructured Meshes for RANS Solutions of Aeronautical Configurations.Antonis F. Antoniadis a, * ,P a n a g i o t i sT s o u t s a n i s referenced data and discussed in terms of accuracy, grid dependence and computational budget.

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Navier-Stokes computations and experimental comparisons for multielement airfoil configurations

Abstract: Abstract

Cited by 43 publications

References 19 publications

Comparative Numerical Analysis of High Lift Airfoils and Effect of Mach Numbers Using CFD

Comparative Numerical Analysis of High Lift Airfoils and Effect of Mach Numbers Using CFD

Grid Quality and Resolution Issues from the Drag Prediction Workshop Series

Assessment of high-order finite volume methods on unstructured meshes for RANS solutions of aeronautical configurations

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