Example of Results windowΒΆ

Warning

This is work in progress

This is file that shows an example of the results window of the pymfoil analysis tool.

Results window of the pymfoil analysis tool

The analyis is for a NACA4415 airfoil at 2.5 degrees angle of attack with 200 panels, at Reynolds number: 5e+6.

The results window displays various aerodynamic coefficients and parameters, including:

  • Lift Coefficient (Cl): 0.758

  • Drag Coefficient (Cd): 0.005841

  • Moment Coefficient (Cm): -0.1043

The image displays:

  • at the bottom half: the airfoil geometry and ?(The flow lines?)??

  • at the top half: (?) the pressure coefficient distribution along the airfoil surfaces .