# fix for zero rotor speed
if n>0.0:
J = V / n * D
# From http://m-selig.ae.illinois.edu/pubs/BrandtSelig-2011-AIAA-2011-1255-LRN-Propellers.pdf
C_T = max(.12 - .07*max(0, J)-.1*max(0, J)**2, 0)
thrusts.append(C_T * self.rho * n**2 * D**4)
else:
thrusts.append(0.0)
The code in get_propeler_thrust should be: