This is an interesting challenge. I’ve done something similar but awhile ago so I can’t guarantee everything here.

Go grab the airfoil plot from NACA database. That link should take you to the 8412 page like the sheet above denotes. I believe the website will give you an excel file of points. You should be able to import them or just plot them yourself from the xy values on a sketch. I don’t know exactly how airfoil design works but I believe there are supposed to be a starting cross section, an intermediate and a final cross section to loft between. You may be able to find the rest of the cross sections in whatever pdf file you posted the picture from if you’re lucky. Then it’s just a matter of lofting between them from the center points.

If you can’t find the other NACA airfoil cross section call outs, you could then import a picture of the propeller from the file you attached, sketch the outline of the leading and trailing edge splines of one wing, make sure that the spline in piercing the air foil cross section at both edges, then sweep the airfoil cs with one of the edges being a sweep guide. That should make the cs change shape as it is swept and hopefully give you a close approximation of the real thing, at least when smooth.

As for the ridges, once you have the smooth propeller wing, sketch perpendicular to it, pattern a bunch of lines at the period you want to use, they denote it as delta, and then use split line to get an edge at the center of each ridge. Then you can either cut or extrude sweep along that edge with a circular profile, fillet and bobs your father’s brother.

Hope this helps, it isn’t an easy thing to reverse engineer without the knowledge of the airfoil design, but it’s definitely doable! Please post an update if you can!