Unswept Wings: lift and induced drag coefficients (calculation)

Calculation template

How does it work?

This calculation template uses Prandtl’s classical Lifting-line Theory.

All the results are available for angles of attack from 0 to 15 degrees and are presented in chart and table formats:

  • Wing / Appendage coefficients: CL, CDi, e (Oswald’s efficiency factor);

Standalone wing (Gap = Yes)

Wing attached to a solid surface (Gap = No)

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