Airfoils.Pro
database / Other families / NACA M5 AIRFOIL
CAMBEREDOTHER FAMILIESSELIG-DATABASE

NACA M5 AIRFOIL

Cambered · 8% thick · low-to-mid Re
Compare↓ Download
PROFILENACA M5 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.2% @ 31%c
max camber2.1% @ 30%c
LE radius0.74%c
area upper / chord0.0390
area lower / chord-0.0196
area camber / chord0.0097
TE thickness0.63%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7726-50.14043.3331.05411.671.96720ClAngle 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 0.05112% of chord; maximum error 0.272%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
122.5
Angle at maximum lift / drag (°)
10
Minimum Cd
0.006901
Maximum Cl
1.738
Angle at maximum Cl (°)
16
Cd at zero lift
0.006908
Cm at zero angle
0.007836
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…