Airfoils.Pro
database / Other families / NACA M26 AIRFOIL
CAMBEREDOTHER FAMILIESSELIG-DATABASE

NACA M26 AIRFOIL

Cambered · 8% thick · low-to-mid Re
Compare↓ Download
PROFILENACA M26 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.3% @ 39%c
max camber8.2% @ 30%c
LE radius0.76%c
area upper / chord0.0732
area lower / chord0.0155
area camber / chord0.0444
TE thickness0.48%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.2836-50.51523.3331.31411.672.11320ClAngle 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 0.07596% of chord; maximum error 0.3358%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
148.4
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006933
Maximum Cl
1.913
Angle at maximum Cl (°)
12
Cd at zero lift
0.02081
Cm at zero angle
-0.05027
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…