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NASA SC(2)-0406 AIRFOIL

Symmetric · 6% thick · low-to-mid Re
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PROFILENASA SC(2)-0406 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.0% @ 35%c
max camber-0.4% @ 100%c
LE radius0.40%c
area upper / chord0.0215
area lower / chord-0.0193
area camber / chord0.0011
TE thickness0.39%c
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Polars

Preliminary
NeuralFoil
-0.6387-50.22793.3331.09411.671.96120ClAngle 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.

Geometry fit: RMS error 0.005814% of chord; maximum error 0.042%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
120.5
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006492
Maximum Cl
1.744
Angle at maximum Cl (°)
16
Cd at zero lift
0.006492
Cm at zero angle
-0.04313
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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