2020
DOI: 10.1002/we.2573
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A two‐dimensional quantitative parametric investigation of simplified surface imperfections on the aerodynamic characteristics of a NACA 633‐418 airfoil

Abstract: The aerodynamic performance of a NACA 633‐418 airfoil has been analyzed with disturbances in approximately 1000 different configurations focused on the frontal 10% of the airfoil. The configuration parameters are based on field test samples and rain erosion test specimens. The most important trends are presented by 500 configurations each simulated for 6°, 8°, and 10° angle of attack. The simulations are performed with the DTU Wind Energy in‐house 2D CFD Reynolds‐averaged Navier–Stokes solver, EllipSys2D, comb… Show more

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Cited by 10 publications
(5 citation statements)
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“…However, smoothening the edges with tapes and creating 45° edges resulted in relatively small reduction in C l , max compared to the clean case. However, in the linear lift region, the difference in C l between the 45° and 90° edges is just 0.01 ( 1%) at 8° AoA, which agrees well with the findings based on computational fluid dynamics (CFD) and shown in Krog Kruse et al 26 . Furthermore, the penalty on C d compared to the clean case was on the other hand severe no matter how the bottom and the edges of the cavity were shaped and C d at low AoAs more than doubled.…”
Section: Resultssupporting
confidence: 91%
“…However, smoothening the edges with tapes and creating 45° edges resulted in relatively small reduction in C l , max compared to the clean case. However, in the linear lift region, the difference in C l between the 45° and 90° edges is just 0.01 ( 1%) at 8° AoA, which agrees well with the findings based on computational fluid dynamics (CFD) and shown in Krog Kruse et al 26 . Furthermore, the penalty on C d compared to the clean case was on the other hand severe no matter how the bottom and the edges of the cavity were shaped and C d at low AoAs more than doubled.…”
Section: Resultssupporting
confidence: 91%
“…Furthermore, wall‐modelling turbulence closures to computational fluid dynamics (CFD) models are unvalidated for roughness applications. A study of simplified surface roughness representations on the NACA 63 3 ‐418 airfoil was undertaken by Krog Kruse et al 13 using the DTU Wind Energy CFD Reynolds‐Averaged Navier–Stokes (RANS) solver, EllipSys2D. An up to 35% reduction in lift and 90% lift‐to‐drag ratio reduction was found, depending on how extensive the surface imperfections were.…”
Section: Introductionmentioning
confidence: 99%
“…The present work aims at elucidating the noise reduction mechanisms of finlet rails for TBL-TE noise. To the purpose, a benchmarked NACA 63 3 − 018 airfoil was adopted for this study [32], as representative of a typical airfoil for wind turbine applications [33,34]. The study is organized as follows.…”
Section: Introductionmentioning
confidence: 99%