Make it lift 800 N per metre.
within 2 % · |C_m,c/4| < 0.08
The challenge
Before you start
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Workspace
Why it happens
The model & its limits
Is the result credible?
Numerical checks and model limits
Computation details
Surface pressure
Across the sweep
The aerodynamic centre is the regression slope of the pitching moment against lift, subtracted from the quarter chord. Thin-airfoil theory says 0.25; thickness moves it slightly aft. The fit's R² is shown because a straight line through a curve is not a point.
All results
No drag and no lift-to-drag ratio: this model is inviscid, so both are zero and a ratio of zeroes is not a metric. The chordwise force that does come out of the pressure integration is in the verification panel, where it belongs — it is an error bar.