Unswept Wings: coefficients, forces, circulation, lift per unit span, and downwash (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);
  • Wing / Appendage forcers: lift, lift-induced drag;
  • Spanwise section lift coefficients (Cl);
  • Spanwise Circulation distribution;
  • Lift per unit span (L’);
  • Induced drag per unit span (D’);
  • Spanwise induced angle of attack;
  • Spanwise downwash velocity;
  • Spanwise chord lengths;

Standalone wing geometry (Gap = Yes)

Wing attached to a solid surface geometry (Gap = No)

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