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NACA M23 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILENACA M23 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.1% @ 31%c
max camber6.4% @ 30%c
LE radius0.73%c
area upper / chord0.0622
area lower / chord0.0044
area camber / chord0.0333
TE thickness0.54%c
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Polars

Preliminary
NeuralFoil
-0.3557-50.35193.3331.05911.671.76720ClAngle 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 0.06723% of chord; maximum error 0.3283%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
145.8
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006645
Maximum Cl
1.59
Angle at maximum Cl (°)
10
Cd at zero lift
0.00863
Cm at zero angle
-0.01956
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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