Thrust Required Calculator

Calculate thrust required for steady level flight and analyze drag components.

Typical: 0.020-0.030 for clean aircraft
Typical: 0.7-0.85
Wingspan² / Wing Area

Thrust & Drag Equations

Thrust Required = Total Drag:

T = D = q x S x CD

Total Drag Coefficient:

CD = CD0 + CL²/(pi x e x AR)

L/D Max:

(L/D)max = 0.5 x sqrt(pi x e x AR / CD0)