Blade Element Momentum Theory (BEMT) Calculator

Thrust generated by a blade element (dT):

Air density (ρ):

Local velocity (v):

Blade chord (c):

Thrust coefficient (C_T):

Radial length of the blade element (dr):

How This Is Calculated

$$ dT = \frac{1}{2} \rho v^2 c C_T dr $$ where:

dT = Thrust generated by a blade element (N)

ρ = Air density (kg/m³)

v = Local velocity (m/s)

c = Blade chord (m)

C_T = Thrust coefficient (dimensionless)

dr = Radial length of the blade element (m)

Assumptions

The system is in steady state.
The fluid is incompressible.
Airfoil behabiour is ideal.
Airfoil section of blade is thin.
There is no flow seperation.

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Thrust Equation

Helix Angle

Induced Drag

Induced Velocity

Propeller Efficiency