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AIRCRAFT AND CLASSICCAMBEREDSELIG-DATABASE

KC135D

Cambered · 9% thick · low-to-mid Re
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PROFILEKC135D
surfacecamber line
GEOMETRY · AREA METRICS
max thickness9.0% @ 40%c
max camber2.0% @ 30%c
LE radius0.89%c
area upper / chord0.0440
area lower / chord-0.0158
area camber / chord0.0141
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
NeuralFoil
-0.5412-50.069153.3330.679611.671.2920ClAngle 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 0.01946% of chord; maximum error 0.07603%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10

Curve summary

NeuralFoil · Within -5° to 20°

Maximum lift / drag
133.3
Angle at maximum lift / drag (°)
6
Minimum Cd
0.005887
Maximum Cl
1.137
Angle at maximum Cl (°)
8
Cd at zero lift
0.005908
Cm at zero angle
-0.04043
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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