AeroSurrogate Studio

Polar analysis

Angle-of-attack sweeps from batched surrogate inference: lift curve, drag polar, efficiency and pitching moment.

Design
NACA 2412 Edit
Sweep
AoA range-4° → 15°
Step
m/s
3194
Re = 3.23 × 10⁶
Overlay saved designs

Save designs from the Studio to compare their polars here.

Cl max
(L/D) max
Cd min
Zero-lift α₀
Cl = 0 crossing

Lift curve

Cl vs α · shaded band = ±1σ

0.00.30.50.81.000.20.40.60.81α (°)Cl
No data

Drag polar

Cl vs Cd (counts)

0.00.30.50.81.00.00.20.40.60.81.0Cd (counts)Cl
No data

Efficiency

L/D vs α

0.000.250.500.751.0000.20.40.60.81α (°)L/D
No data

Pitching moment

Cm about quarter chord vs α

0.000.250.500.751.0000.20.40.60.81α (°)Cm¼
No data