How is d(Cl)/d(alpha)@stall and Cl increment to stall defined in Xrotor?
I interpreted the values as follows:


The angle of attack at which the specified propeller airfoil generates zero lift
The change in lift coefficient per change in $\alpha$ in radians
The same as 2, except that it is this value around the stall angle (it is mostly a safety factor for numerical calculations I think, small but non-zero)
Maximum $C_l$, which is achieved at the theoretical stall angle
Minimum $C_l$, which occurs on the backwards sweep of the propeller
The $C_l$ increment from the last linear part of the $C_l$ polar to the stall point
The $C_d$ at $\alpha=0$
The $C_l$ at $\alpha=0$
Quadratic drag dependence on $C_l$, slope of the $C_d,C_l^2$ curve
The Reynolds number at which these values are obtained
Re scaling exponent as explained in the XRotor documentation
Moment coefficient $C_m$
The critical Mach number.