Flow simulation over an Airfoil
Aim: 2D flow simulation over NACA0017
Objectives:
1) Modeling the airfoil and flow simulation setup
2) Comparing flow at various angle of attacks (0, 2, 4, 6, 8, 10)
Procedure:
1) Airfoil curve was first imported.
2) The curve was extruded to generate a 3D body
3) 2D Mesh was setup along the crossection
4) A 200m/s flow was introduced going from the leading edge towards the trailing edge.
5) Parametric study was conducted using angle of attack as the variable.
6) Frontal area was calculated using the projection of the solid for each angle of attack.
Results:
1) Surface Force along Y direction:
2) Surface Force along X direction:
Post Processing:
The forces thus obtained from the analysis were used to determine the aerodynamic coefficients and were plotted.
cl vs alpha:
Note: Drop in cl after 8 degree angle of attack indicates stall
cd vs alpha:
Drag Polar:
Discussion:
The plots obtained from post processing data concur with available experimental data, therefore one can say that the constraints and parameters used in the simulation are valid.
References: