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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

KC-135 BL124.32 AIRFOIL

Cambered · 13% thick · low-to-mid Re
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PROFILEKC-135 BL124.32 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness13.0% @ 39%c
max camber1.6% @ 20%c
LE radius1.85%c
area upper / chord0.0527
area lower / chord-0.0318
area camber / chord0.0105
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6239-50.009673.3330.643311.671.27720ClAngle 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.

The compressibility correction is a low-fidelity estimate, not a resolved shock or compressible CFD solution.

Geometry fit: RMS error 0.02208% of chord; maximum error 0.09342%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
118.8
Angle at maximum lift / drag (°)
6
Minimum Cd
0.006411
Maximum Cl
1.118
Angle at maximum Cl (°)
8
Cd at zero lift
0.00644
Cm at zero angle
-0.02182
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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