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S1020 Ornithopter airfoil

Cambered · 15% thick · low-to-mid Re
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PROFILES1020 Ornithopter airfoil
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.1% @ 34%c
max camber5.0% @ 52%c
LE radius2.51%c
area upper / chord0.0849
area lower / chord-0.0139
area camber / chord0.0355
TE thickness0.00%c
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Polars

Preliminary
NeuralFoil
0.009045-50.61373.3331.21811.671.82320ClAngle of attack (°)
Why this curve

This is a NeuralFoil prediction from the stored profile coordinates and the selected flow condition, with AeroSandbox compressibility corrections. It is not a completed OpenFOAM calculation.

Prediction error has not been calibrated for this condition. No accuracy interval is claimed.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.02211% of chord; maximum error 0.08041%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
147.5
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006897
Maximum Cl
1.672
Angle at maximum Cl (°)
9
Cd at zero lift
—
Cm at zero angle
-0.1811
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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