# NACA0012 airfoil

(Difference between revisions)
 Revision as of 18:40, 10 November 2009 (view source)Jack1980 (Talk | contribs)← Older edit Revision as of 18:42, 10 November 2009 (view source)Jack1980 (Talk | contribs) Newer edit → Line 1: Line 1: == Introduction == == Introduction == The NACA 0012 airfoil is widely used. The simple geometry and the large amount of wind tunnel data provide an excellent 2D validation case. For this case I use the Spalart-Allmaras turbulence model. The NACA 0012 airfoil is widely used. The simple geometry and the large amount of wind tunnel data provide an excellent 2D validation case. For this case I use the Spalart-Allmaras turbulence model. - - == Mesh ==

+ == Mesh == + [[Image:Naca0012 mesh final.JPG]] [[Image:Naca0012 mesh final.JPG]]

The mesh is a 30,000 cell C-grid. The width off the first cell at the foil boundary is 0.02 mm. At Re = 3e6 this results in a wall y+ = 1.3 ± 0.4 . The mesh shown is for an Angle of Attack of 6 degrees. The mesh is a 30,000 cell C-grid. The width off the first cell at the foil boundary is 0.02 mm. At Re = 3e6 this results in a wall y+ = 1.3 ± 0.4 . The mesh shown is for an Angle of Attack of 6 degrees. - - == Drag Coefficient ==

+ == Drag Coefficient == + [[Image:Naca0012 cd tripwire.JPG]] [[Image:Naca0012 cd tripwire.JPG]]

The drag coefficient at zero Angle of Attack depends on the Reynold's number. The experimental data is for an airfoil with a trip wire that forces the experimental boundary layer to be completely turbulent.[1] This corresponds to the Fluent model, which has an active turbulence model over the complete airfoil. The drag coefficient at zero Angle of Attack depends on the Reynold's number. The experimental data is for an airfoil with a trip wire that forces the experimental boundary layer to be completely turbulent.[1] This corresponds to the Fluent model, which has an active turbulence model over the complete airfoil. - - == Lift Curve ==

+ == Lift Curve == + [[Image:Naca0012 lift curve.JPG]] [[Image:Naca0012 lift curve.JPG]]

The lift coefficient depends on the Angle of Attack. For Re = 2e6 I compare the lift coefficient to experimental results.[2] The lift coefficient depends on the Angle of Attack. For Re = 2e6 I compare the lift coefficient to experimental results.[2] - - == Lift Curve Slope ==

+ == Lift Curve Slope == + [[Image:Naca0012 lift curve slope.JPG]] [[Image:Naca0012 lift curve slope.JPG]]

The initial slope of the lift curve depends on the Reynold's number. Here I compare the lift curve slope to experimental results.[1] The initial slope of the lift curve depends on the Reynold's number. Here I compare the lift curve slope to experimental results.[1] - +
== References == == References == 1. W. J. McCroskey, ''A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil'', NASA Technical Memorandum 10001 9 (1987)
1. W. J. McCroskey, ''A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil'', NASA Technical Memorandum 10001 9 (1987)
2. L. Lazauskus, [http://http://www.cyberiad.net/library/airfoils/foildata/n0012cl.htm NACA 0012 Lift Data] 2. L. Lazauskus, [http://http://www.cyberiad.net/library/airfoils/foildata/n0012cl.htm NACA 0012 Lift Data]

## Introduction

The NACA 0012 airfoil is widely used. The simple geometry and the large amount of wind tunnel data provide an excellent 2D validation case. For this case I use the Spalart-Allmaras turbulence model.

## Mesh

The mesh is a 30,000 cell C-grid. The width off the first cell at the foil boundary is 0.02 mm. At Re = 3e6 this results in a wall y+ = 1.3 ± 0.4 . The mesh shown is for an Angle of Attack of 6 degrees.

## Drag Coefficient

The drag coefficient at zero Angle of Attack depends on the Reynold's number. The experimental data is for an airfoil with a trip wire that forces the experimental boundary layer to be completely turbulent.[1] This corresponds to the Fluent model, which has an active turbulence model over the complete airfoil.

## Lift Curve

The lift coefficient depends on the Angle of Attack. For Re = 2e6 I compare the lift coefficient to experimental results.[2]

## Lift Curve Slope

The initial slope of the lift curve depends on the Reynold's number. Here I compare the lift curve slope to experimental results.[1]

## References

1. W. J. McCroskey, A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil, NASA Technical Memorandum 10001 9 (1987)
2. L. Lazauskus, NACA 0012 Lift Data