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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asked Jun 6, 2018 at 20:54
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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°. $\endgroup$– Cpt ReynoldsJun 6, 2018 at 21:45
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1$\begingroup$ Got to be a typo. You can't get to Max Cl at 12.5deg if the wing stalls at -0.5deg $\endgroup$– PilotheadJun 6, 2018 at 21:51
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1 Answer
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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:
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.
answered Jun 6, 2018 at 22:17