ccblade.CCAirfoil.evaluate

CCAirfoil.evaluate(alpha, Re, return_cm=False)

Get lift/drag coefficient at the specified angle of attack and Reynolds number. Parameters ———- alpha : float (rad)

angle of attack

Re : float

Reynolds number

cl : float

lift coefficient

cd : float

drag coefficient

This method uses a spline so that the output is continuously differentiable, and also uses a small amount of smoothing to help remove spurious multiple solutions.