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database / NACA 6-series / NACA 65(1)-212 a=0.6
CAMBEREDNACA 6-SERIESSELIG-DATABASE

NACA 65(1)-212 a=0.6

Cambered · 12% thick · low-to-mid Re
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PROFILENACA 65(1)-212 a=0.6
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 40%c
max camber1.5% @ 50%c
LE radius1.58%c
area upper / chord0.0486
area lower / chord-0.0291
area camber / chord0.0098
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6396-50.21853.3331.07711.671.93520ClAngle 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 0.02716% of chord; maximum error 0.113%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
126.9
Angle at maximum lift / drag (°)
10
Minimum Cd
0.006865
Maximum Cl
1.72
Angle at maximum Cl (°)
16
Cd at zero lift
0.006884
Cm at zero angle
-0.03452
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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