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USA 25 AIRFOIL

Cambered · 8% thick · low-to-mid Re
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PROFILEUSA 25 AIRFOIL
surfacecamber line
GEOMETRY · AREA METRICS
max thickness8.3% @ 20%c
max camber5.2% @ 30%c
LE radius0.76%c
area upper / chord0.0628
area lower / chord-0.0010
area camber / chord0.0309
TE thickness0.00%c
DOWNLOAD COORDINATES

Polars

Preliminary
Combined estimate
-0.3834-50.31123.3331.00611.671.70120ClAngle of attack (°)
Why this curve

This curve combines the stored NeuralFoil prediction with 2 contributing CFD observations. History windows remain observations, not separate solver runs or automatically converged points.

Model uncertainty is conditional on the stated assumptions and has not been calibrated for this condition. It is not a validated accuracy guarantee.

Geometry fit: RMS error 0.06796% of chord; maximum error 0.3588%.

NeuralFoil 0.3.3 · AeroSandbox 4.2.10 · Polar model progressive-polar-gp-v2

  • · Converged
  • · Provisional history

Curve summary

Combined estimate · Within -5° to 20°

Maximum lift / drag
57.87
Angle at maximum lift / drag (°)
9
Minimum Cd
0.02393
Maximum Cl
1.527
Angle at maximum Cl (°)
10
Cd at zero lift
0.04187
Cm at zero angle
-0.06372
CFD points
SOLVER WORK0 conditions · 0 engine jobs
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