# -*- coding: utf-8 -*-
"""Calculations with airfoils
"""
[docs]def get_lift(air_df, wsp, rho=1.225):
"""Determine the lift of an airfoil
Parameters
-----------
air_df : pd.Dataframe
Pandas Dataframe containing x- and y-coordinates of airfoil data.
wsp : int, float
Velocity of air..
rho : int, float
Density of air.
"""
c_l = 0.2 # life coefficeint, this is made-up
area = (air_df.x.max() - air_df.x.min()) * \
(air_df.y.max() - air_df.y.min()) # also made up
lift_force = 0.5 * c_l * rho * wsp**2 * area # equation for lift force
return lift_force