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NASA SC(2)-0710 AIRFOIL

Symmetric · 10% thick · low-to-mid Re
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PROFILENASA SC(2)-0710 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 37%c
max camber-1.4% @ 100%c
LE radius1.10%c
area upper / chord0.0358
area lower / chord-0.0316
area camber / chord0.0021
TE thickness0.49%c
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Polars

Preliminary
NeuralFoil
-0.2852-50.57643.3331.43811.672.320ClAngle 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 0.01384% of chord; maximum error 0.04774%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
141.1
Angle at maximum lift / drag (°)
8
Minimum Cd
0.007261
Maximum Cl
2.084
Angle at maximum Cl (°)
15
Cd at zero lift
0.007265
Cm at zero angle
-0.128
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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