1. Flight Conditions
2. Angle of Attack Range
3. Lift Coefficient (Cl) Curve
Enter control points as "alpha,value" (e.g., "5.0,1.2") or click on the chart to add points. The spline will interpolate between points.
4. Lift-to-Drag Ratio (Cl/Cd) Curve
Enter control points as "alpha,value" (e.g., "5.0,100.0") or click on the chart to add points. The spline will interpolate between points.
5. Thickness Search Range
The optimization will automatically test different thickness combinations to find the best airfoil. Specify the range of maximum thickness values to search (in 0.01 increments). For each maximum thickness tested, the system will also try all minimum thickness values from 0.01 up to half of that maximum thickness.
Example: If you set 0.10 to 0.20, it will test max thicknesses of 0.10, 0.11, 0.12... up to 0.20. For max thickness 0.20, it will test min thicknesses of 0.01, 0.02, 0.03... up to 0.10 (half of 0.20).