Danijel,
I have a book on airfoil sections for full sized aircraft. The NACA 2412 data is given at a Reynolds number of 3,120,000 and may not be accurate for model sizes. I am a chemical engineer so I can't stand behind any aeronautical calculations. I have some other data and modeling experience that tells me that airfoil results at modeling dimensions follow similar patterns. The data I have shows the stall at 20 to 22 degrees angle of attack for Reynolds number of 3 to 8 million with a lift coefficient of 1.4 to 1.6. Your stall speed will depend on model weight and wing area. I have used NACA 23018 on an original design (looks similar to an amateur designer although much thicker) and it flew very well including aerobatics. I too (like Tall Paul) suspect the 2412 would work well on your model. If you need stations to plot the airfoil you can send a PM and I will copy for you.

I just looked deeper into my collection of data and found a hand drawn graph comparing Clark Y and 2412 at Reynolds number of 80,000--model size data. Can't remember where I got it. Clark Y stalls at 10 degrees AOA with lift coefficient of 1.0. 2412 stalls at 12 degrees AOA with lift coef of 1.2. I would say the 2412 is a better choice for your model.
Chuck