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NASA SC(2)-0404 AIRFOIL

Symmetric · 4% thick · low-to-mid Re
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PROFILENASA SC(2)-0404 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness4.0% @ 37%c
max camber0.5% @ 81%c
LE radius0.18%c
area upper / chord0.0150
area lower / chord-0.0122
area camber / chord0.0014
TE thickness0.28%c
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Polars

Preliminary
Combined estimate
-0.6037-50.019933.3330.643611.671.26720ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 0 contributing CFD observations. History windows remain observations, not separate solver runs or automatically converged points.

Model uncertainty is conditional on the stated assumptions and has not been calibrated for this condition. It is not a validated accuracy guarantee.

Geometry fit: RMS error 0.004716% of chord; maximum error 0.03807%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10 · Polar model progressive-polar-gp-v2

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
104.6
Angle at maximum lift / drag (°)
4
Minimum Cd
0.00567
Maximum Cl
1.111
Angle at maximum Cl (°)
18
Cd at zero lift
0.005688
Cm at zero angle
-0.0506
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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