aerodynamics simulation of NACA 2414 airfoil
Airfoil has been simulated at different angle of attacks as follows-
0 degree-
5 degrees-
10 degrees-
15 degrees-
20 degrees-
Frontal area has been calculated by calculating area of y-z plane of bounding box.
Pressure and velocity profiles for different angle of attack are as follows using k-w model-
0 degrees angle of attack-
pressure profile-
velocity profile-
5 degrees angle of attack-
pressure profile-
velocity profile-
10 degrees angle of attack-
pressure profile-
velocity profile-
15 degrees angle of attack-
pressure profile-
velocity profile-
20 degrees angle of attack-
pressure profile-
velocity profile-
Values of forces,velocity and density were taken from .out files and average of last 200 values was done to calculate values of cl and cd.
formulas used for Cl and Cd are as follows:-
Cl=2 X Lift Force/(Density X (Velocity)^2 X Frontal area)
Cd=2 X Drag Force/(Density X (Velocity)^2 X Frontal area)
k-omega SST model-
RNG-Epsilon Model-