AR = 4.40 / 5.61 (+ep) · e = 0.85 · S = 0.2750 m² · q = 551 Pa @ 30 m/s
Polar Curves
37 points
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Aerodynamic Analysis
Cp & force field at α = 4.0°
Cp distribution
Pressure coefficient along chord
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Pressure distribution, α = 4°
Pressure vectors
Surface-normal force field (CPV-style)
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Pressure vectors, α = 4°
Transition location
Laminar → turbulent boundary-layer state
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Boundary-layer health
Shape factor H + skin friction Cf diagnostics
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Separation bubbles
Laminar separation regions and trailing-edge stall
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Polar Data
full sweep · design point highlighted
α°CLCDCML/D
XFOIL results are 2D section data: CD and L/D do not include induced drag: a real 3D wing is significantly less efficient. The 3D estimates above apply a finite-wing correction (AR with endplate credit, Oswald e = 0.85) and your wing geometry (span × chord × ½ρV²) to turn coefficients into forces.
Sign convention: this wing runs in downforce orientation: negative CL is force toward the ground, positive CM follows the same flipped frame. Ncrit = 9 models a clean free-stream (standard wind-tunnel turbulence); near and past stall (here α > 13.5°) XFOIL's 2D boundary-layer model becomes optimistic. For the separated regime, see what the CFD tool reports on the same wing.
Screen airfoils in seconds: this exact report, every run
Pick or design an airfoil, set Re and the angle range, and get a full viscous polar with 3D force estimates, Cp distribution and a downloadable .pol file, in seconds, not minutes.