This stats says this airfoil stalls at -0.5°,does this means if I have this airfoil as a wing ,I won't even be able to have a descent aoa?

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  • $\begingroup$ The stall angle entry doesn’t make sense - stall should occur just above the angle for max CL which is given as 12.5°. Max L/D (best glide, not stall) is at -0.5°. $\endgroup$ Jun 6 '18 at 21:45
  • 1
    $\begingroup$ Got to be a typo. You can't get to Max Cl at 12.5deg if the wing stalls at -0.5deg $\endgroup$
    – Pilothead
    Jun 6 '18 at 21:51

Don't believe everything that a computer tells you.

This airfoil is listed in the airfoiltools site, and I took the liberty to copy its XFOIL results here:

Airfoiltools plots for Bartels 35-IIIC

I selected the Reynolds numbers 500,000 and 1,000,000, which should be at the low end for a man-carrying aircraft. As you can see, the stall angle of attack is at 15° and the maximum lift coefficient is between 1.7 and 1.75. To achieve a lift coefficient of 1.89 with that airfoil will need a much higher Reynolds number, but max. L/D is already around 120.


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