Is the airfoil correct?

[jayeye2011]

https://en.wikipedia.org/wiki/Zl%C3%ADn_Z_526
according to the wikipedia the Zlin-526 uses two different airfoils
root: NACA 2418
http://airfoiltools.com/polar/details?polar=xf-naca2418-il-1000000
tip: NACA 4412
http://airfoiltools.com/polar/details?polar=xf-naca4412-il-1000000
The z526afs.tmd file has the same parameters for root and tip
<[airfoil][AirfoilRoot][]
<[float64][Cl0][0.23]>
<[float64][Cd0][0.0067]>
<[float64][Cm0][-0.0345]>
<[float64][ClAlpha][5.500395]>
<[float64][CdAlpha][0.630254]>
<[float64][CmAlpha][0.100268]>
<[float64][ClFlap][2.5]>
<[float64][CdFlap][0.0]>
<[float64][CmFlap][-0.2]>
<[float64][Cd0Base][0.001745]>
<[float64][ClAlphaBase][2.4]>
<[float64][CdAlphaBase][1.8]>
<[float64][CmAlphaBase][-0.45]>
<[float64][ClFlapBase][0.6]>
<[float64][AttachedCenter][0.0]>
<[float64][AttachedRange][0.174533]>
<[float64][StallRange][0.139626]>
<[float64][AttachedCenterFlap][-0.12]>
>
<[airfoil][AirfoilTip][]
<[float64][Cl0][0.23]>
<[float64][Cd0][0.0066]>
<[float64][Cm0][-0.0345]>
<[float64][ClAlpha][5.500395]>
<[float64][CdAlpha][0.630254]>
<[float64][CmAlpha][0.100268]>
<[float64][ClFlap][2.5]>
<[float64][CdFlap][0.0]>
<[float64][CmFlap][-0.2]>
<[float64][Cd0Base][0.006283]>
<[float64][ClAlphaBase][2.4]>
<[float64][CdAlphaBase][1.8]>
<[float64][CmAlphaBase][-0.45]>
<[float64][ClFlapBase][0.6]>
<[float64][AttachedCenter][0.0]>
<[float64][AttachedRange][0.174533]>
<[float64][StallRange][0.139626]>
<[float64][AttachedCenterFlap][-0.12]>
>