Airfoils.Pro
database / Other families / NACA M6
CAMBEREDOTHER FAMILIESSELIG-DATABASE

NACA M6

Cambered · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENACA M6
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 30%c
max camber2.2% @ 30%c
LE radius1.59%c
area upper / chord0.0532
area lower / chord-0.0313
area camber / chord0.0109
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7511-50.08693.3330.924911.671.76320ClAngle 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 0.05736% of chord; maximum error 0.2969%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
111.6
Angle at maximum lift / drag (°)
11
Minimum Cd
0.007221
Maximum Cl
1.553
Angle at maximum Cl (°)
17
Cd at zero lift
0.007246
Cm at zero angle
0.01732
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…