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NACA-M1 AIRFOIL

Symmetric · 6% thick · low-to-mid Re
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PROFILENACA-M1 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.2% @ 30%c
max camber0.0% @ 0%c
LE radius0.42%c
area upper / chord0.0219
area lower / chord-0.0219
area camber / chord0.0000
TE thickness0.40%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.8047-50.081733.3330.968211.671.85520ClAngle 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 0.04018% of chord; maximum error 0.2041%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
114.5
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006458
Maximum Cl
1.633
Angle at maximum Cl (°)
16
Cd at zero lift
0.006458
Cm at zero angle
1.301e-16
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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