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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASETHICK

KC135A

Cambered · 15% thick · low-to-mid Re
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PROFILEKC135A
surfacecamber line
GEOMETRY · AREA METRICS
max thickness15.5% @ 35%c
max camber1.6% @ 20%c
LE radius2.64%c
area upper / chord0.0601
area lower / chord-0.0393
area camber / chord0.0104
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.6342-50.010183.3330.654611.671.29920ClAngle 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 0.0252% of chord; maximum error 0.1071%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
116.2
Angle at maximum lift / drag (°)
7
Minimum Cd
0.006852
Maximum Cl
1.138
Angle at maximum Cl (°)
9
Cd at zero lift
0.006937
Cm at zero angle
-0.01838
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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