Airfoils.Pro
database / S/SC series / NASA SC(2)-0606 AIRFOIL
S/SC SERIESSELIG-DATABASESYMMETRICTHIN

NASA SC(2)-0606 AIRFOIL

Symmetric · 6% thick · low-to-mid Re
Compare↓ Download
PROFILENASA SC(2)-0606 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness6.0% @ 35%c
max camber-1.2% @ 100%c
LE radius0.40%c
area upper / chord0.0209
area lower / chord-0.0196
area camber / chord0.0006
TE thickness0.41%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.41-50.41243.3331.23511.672.05720ClAngle 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 0.008016% of chord; maximum error 0.04066%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
125.6
Angle at maximum lift / drag (°)
7
Minimum Cd
0.00664
Maximum Cl
1.852
Angle at maximum Cl (°)
15
Cd at zero lift
0.006645
Cm at zero angle
-0.0897
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…