53rd AIAA Aerospace Sciences Meeting 2015
DOI: 10.2514/6.2015-0311
|View full text |Cite
|
Sign up to set email alerts
|

RANS and LES/RANS Simulations of Flow Over an Dynamically Pitching Naca0012 Airfoil

Abstract: The hybrid Large-Eddy/Reynolds-Averaged Navier-Stokes (LES/RANS) and RANS simulations are used to investigate the properties of subsonic flow over NACA 0012 airfoils undergoing static and dynamic stall conditions (M=0.1, α=16.7°, Re c =1.0×10 6 ). In the simulations of NACA 0012 airfoil at static stall case, Menter's SST model predicts an attached flow at the leading edge, whereas the Gieseking's LES/RANS model on a coarser mesh predicts a massively separated flow characterized by the stabilization of a detach… Show more

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
1
1

Citation Types

0
3
0

Year Published

2016
2016
2017
2017

Publication Types

Select...
1
1

Relationship

1
1

Authors

Journals

citations
Cited by 2 publications
(3 citation statements)
references
References 31 publications
0
3
0
Order By: Relevance
“…Static-stall predictions for the Aerospatiale 'A-Airfoil' [27], reported in [24], were quite reasonable and similar to those obtained by Mary and Sagaut [35] using a wall-resolved LES. Dynamic stall calculations [25,26], performed for an experiment of Pruski, et al [29] involving pitching of a NACA 0012 airfoil, never achieved this level of success. While other factors (spanwise domain extent, grid resolution, tunnel blockage effects) certainly influenced predictive capability, the fact that the ensemble-averaging strategies employed (variants of weighted exponential time-averaging methods) could not operate properly for a pitching airfoil led to additional uncertainties that could not be completely resolved…”
Section: A2 New Model Formulationmentioning
confidence: 90%
See 1 more Smart Citation
“…Static-stall predictions for the Aerospatiale 'A-Airfoil' [27], reported in [24], were quite reasonable and similar to those obtained by Mary and Sagaut [35] using a wall-resolved LES. Dynamic stall calculations [25,26], performed for an experiment of Pruski, et al [29] involving pitching of a NACA 0012 airfoil, never achieved this level of success. While other factors (spanwise domain extent, grid resolution, tunnel blockage effects) certainly influenced predictive capability, the fact that the ensemble-averaging strategies employed (variants of weighted exponential time-averaging methods) could not operate properly for a pitching airfoil led to additional uncertainties that could not be completely resolved…”
Section: A2 New Model Formulationmentioning
confidence: 90%
“…As Gieseking's model is dependent on both inner-layer and outerlayer length-scale information, it is capable of adjusting to strong departures from local equilibrium and can respond to large changes in the boundary-layer thickness without problem-specific adjustment. The model has been used in simulations of shock / boundary layer interactions [19,20], scramjet combustor calculations [21][22][23], and airfoils undergoing static stall [24] and dynamic stall [25,26].…”
Section: A Les/rans Hybridizationmentioning
confidence: 99%
“…This model is designed to give highly accurate predictions of the onset and the amount of flow separation under adverse pressure gradients by including the transport effects into the formulation of the eddy-viscosity. This results in a major improvement in terms of flow separation predictions, thus appearing very attractive and favorable in compressor industry (Yin et al 2010, Chen et al 2012, Halawa et al 2015, Ke et al 2015and Ameli et al 2016. And a grid dependence study is conducted for the design point.…”
mentioning
confidence: 99%