Rocket Thrust Calculator

Property to Calculate:

Thrust (F):

Mass flow rate of exhaust (m):

Effective exhaust velocity (v_e):

Exit pressure (p_e):

Ambient pressure (p₀):

Exhaust area (A_e):

How This Is Calculated

$$ F = m V_e + (p_e - p_0)A_e $$ where:

F = Thrust (N)

m = Mass flow rate of exhaust (kg/s)

v_e = Effective exhaust velocity (m/s)

p_e = Exit pressure (Pa)

p₀ = Ambient pressure (Pa)

A_e = Exhaust area (m²)

Assumptions

The exhaust and mass flow rate are in steady flow.
Exhaust flow is uniform.
Nozzle exit area remains constant.
Ambient pressure is uniform.
Nozzle operation is ideal.

Related Calculators

Specific Impulse

Rocket Equation

Rocket Equation with Gravity Loss