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NASA/LANGLEY RC-08(N)1 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILENASA/LANGLEY RC-08(N)1 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.0% @ 38%c
max camber1.6% @ 26%c
LE radius0.71%c
area upper / chord0.0349
area lower / chord-0.0179
area camber / chord0.0085
TE thickness0.13%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7475-50.13553.3331.01811.671.90120ClAngle 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 0.01582% of chord; maximum error 0.08993%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
119.7
Angle at maximum lift / drag (°)
9
Minimum Cd
0.006353
Maximum Cl
1.681
Angle at maximum Cl (°)
16
Cd at zero lift
0.006379
Cm at zero angle
0.007047
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…