def aero_force(rho, V, C, A):
	"""
	Aerodynamic lift/drag equation

	Input variables:
		rho	:	Fluid density
		V	:	Fluid velocity
		C 	: 	Lift/drag coefficient
		A 	: 	Reference area
	"""

	F = 0.5 * rho * (V**2) * C * A

	return F