Airfoils.Pro
database / S/SC series / NASA SC(2)-0012 AIRFOIL
S/SC SERIESSELIG-DATABASESYMMETRIC

NASA SC(2)-0012 AIRFOIL

Symmetric · 12% thick · low-to-mid Re
Compare↓ Download
PROFILENASA SC(2)-0012 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness12.0% @ 37%c
max camber0.0% @ 0%c
LE radius1.59%c
area upper / chord0.0426
area lower / chord-0.0426
area camber / chord0.0000
TE thickness0.60%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.8371-50.099153.3331.03511.671.97220ClAngle 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 0.01339% of chord; maximum error 0.04396%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
124.9
Angle at maximum lift / drag (°)
11
Minimum Cd
0.007211
Maximum Cl
1.738
Angle at maximum Cl (°)
17
Cd at zero lift
0.007211
Cm at zero angle
6.863e-17
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…