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NACA M27 AIRFOIL

Cambered · 12% thick · low-to-mid Re
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PROFILENACA M27 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.9% @ 31%c
max camber8.4% @ 30%c
LE radius1.57%c
area upper / chord0.0873
area lower / chord0.0031
area camber / chord0.0452
TE thickness0.52%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.2519-50.50223.3331.25611.672.01120ClAngle 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 0.07897% of chord; maximum error 0.3559%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
136.5
Angle at maximum lift / drag (°)
7
Minimum Cd
0.00732
Maximum Cl
1.822
Angle at maximum Cl (°)
12
Cd at zero lift
0.02309
Cm at zero angle
-0.05281
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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