Airfoils.Pro
database / Other families / NACA M21 AIRFOIL
CAMBEREDOTHER FAMILIESSELIG-DATABASE

NACA M21 AIRFOIL

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA M21 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness11.9% @ 30%c
max camber6.0% @ 30%c
LE radius1.57%c
area upper / chord0.0756
area lower / chord-0.0087
area camber / chord0.0334
TE thickness0.48%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.3125-50.42083.3331.15411.671.88720ClAngle 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 0.0695% of chord; maximum error 0.3274%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
142
Angle at maximum lift / drag (°)
8
Minimum Cd
0.006934
Maximum Cl
1.704
Angle at maximum Cl (°)
11
Cd at zero lift
0.01119
Cm at zero angle
-0.05205
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…