Calculate the pressure thrust, propeller thrust, or rocket thrust. Select the correct tab and enter the required information.

Thrust Calculator
Pressure thrust
Propeller thrust
Rocket thrust
This is the simplest thrust setup most visitors expect. Enter pressure difference and either area or diameter.
Pressure + area
Pressure + diameter
Use gauge pressure or pressure difference across the surface.
This tab estimates static propeller thrust using a thrust-coefficient method. It is best for quick comparisons, not flight-test accuracy.
Conservative
Typical
Aggressive
This keeps your original advanced rocket-style equation with optional pressure correction.
Mass flow rate
Mass + burn time
Pressure correction

Thrust Formula

The following formula is used to calculate the thrust force produced by a rocket engine.

T = ṁ Ve + (Pe − Pa) Ae

  • ṁ – propellant mass-flow rate (kg/s)
  • Ve – effective exhaust (exit) velocity relative to the rocket (m/s)
  • Pe – static pressure at the nozzle exit (Pa)
  • Pa – ambient (back-) pressure (Pa)
  • Ae – exit area of the nozzle (m²)

Thrust Definition

Thrust is the force produced by an engine (such as a rocket or jet) when it expels mass as exhaust. For a rocket nozzle, thrust includes both the exhaust momentum term (ṁVe) and the nozzle pressure-difference term (Pe − Pa)Ae.

Thrust Example

How to calculate thrust?

  1. First, determine the exhaust velocity.

    Use the effective exhaust (exit) velocity Vₑ relative to the rocket (or use an Isp preset to compute Vₑ = Isp×g₀).

  2. Next, determine the propellant mass flow.

    Measure the propellant mass used (Δm) over a burn time (Δt), then compute ṁ = Δm/Δt.

  3. Next, determine the pressure/area terms.

    Find the nozzle exit pressure Pₑ, ambient pressure Pₐ, and nozzle exit area Aₑ (or set Pₑ = Pₐ to neglect the pressure-thrust term).

  4. Finally, calculate the thrust.

    Compute T = ṁVₑ + (Pₑ − Pₐ)Aₑ.

FAQ

What is thrust?

Thrust is the force produced by an engine when it expels mass (exhaust). For rocket nozzles, it includes both the exhaust momentum term and (when applicable) a nozzle pressure-difference term.