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RAE 101 AIRFOIL

Symmetric · 10% thick · low-to-mid Re
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PROFILERAE 101 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness10.0% @ 30%c
max camber0.0% @ 0%c
LE radius1.10%c
area upper / chord0.0321
area lower / chord-0.0321
area camber / chord0.0000
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.7916-50.098243.3330.988111.671.87820ClAngle 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 0.004893% of chord; maximum error 0.02436%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
119.9
Angle at maximum lift / drag (°)
11
Minimum Cd
0.006715
Maximum Cl
1.655
Angle at maximum Cl (°)
17
Cd at zero lift
0.006715
Cm at zero angle
1.601e-16
CFD points
SOLVER WORK0 conditions · 0 engine jobs
Loading solver work…