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Airfoil Lab
A quasi-steady thin-airfoil model with an induced-drag polar. Sweep the controls and watch lift, drag and the stall boundary respond.
Fig. 01 — Flow fieldAttached flow
- 65.5 kN
- Lift
- 4.10 kN
- Drag
- 16.0
- L/D
- 0.910
- C_L
- 0.0569
- C_D
- 3.00 kPa
- Dynamic pressure q
Engineer's insight
Lift scales with the square of velocity but only linearly with angle of attack — and only until the boundary layer separates. Past roughly 15°, additional incidence destroys lift and multiplies drag.
Controls
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