Airfoils.Pro
database / S/SC series / NASA SC(2)-0410 AIRFOIL
CAMBEREDS/SC SERIESSELIG-DATABASE

NASA SC(2)-0410 AIRFOIL

Cambered · 10% thick · low-to-mid Re
Compare↓ Download
PROFILENASA SC(2)-0410 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 38%c
max camber1.2% @ 85%c
LE radius1.09%c
area upper / chord0.0374
area lower / chord-0.0301
area camber / chord0.0037
TE thickness0.49%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6042-50.32913.3331.26211.672.19620ClAngle 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 0.0121% of chord; maximum error 0.04324%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
135.1
Angle at maximum lift / drag (°)
10
Minimum Cd
0.007132
Maximum Cl
1.962
Angle at maximum Cl (°)
17
Cd at zero lift
0.007136
Cm at zero angle
-0.07275
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…