NACA0012 airfoil
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(New page: == 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 Spala...) |
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== Mesh == | == Mesh == | ||
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| - | + | [[Image:Naca0012 mesh final.JPG]] | |
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| - | 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 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 == | ||
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| - | + | [[Image:Naca0012 cd tripwire.JPG]] | |
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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. | ||
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== Lift Curve == | == Lift Curve == | ||
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| - | + | [[Image:Naca0012 lift curve.JPG]] | |
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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] | ||
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== Lift Curve Slope == | == Lift Curve Slope == | ||
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| - | + | [[Image:Naca0012 lift curve slope.JPG]] | |
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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] | ||
Revision as of 18:40, 10 November 2009
Contents |
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
