Use this engineering calculation for a transparent preliminary estimate or independent arithmetic check when geometry, materials, loads, operating conditions, and units are defined consistently.

Mass Flow Kilograms Per Second (kg/s)

Required number input.

Exhaust Speed Meters Per Second (m/s)

Required number input.

Exit Pressure Pascals (Pa)

Required number input.

Ambient Pressure Pascals (Pa)

Required number input.

Exit Area Square Meters (m²)

Required number input.

Ideal rocket thrust ṁve+(pe−pa)Ae from exhaust momentum and nozzle pressure imbalance. The tool evaluates the supplied inputs together and returns the named outputs below; it does not infer omitted operating conditions or change the units shown.^[1]

Thrust Newtons (N)

The resulting thrust newtons returned as a number.

• Rocket thrust and specific impulse depend on mass flow, chamber and ambient pressure, nozzle expansion, propellant state, mixture ratio, combustion efficiency, and operating altitude. Ideal equations do not establish structural, thermal, stability, or mission performance.
• Use finite inputs in the displayed units and preserve more precision than the final presentation requires. Independently verify safety-critical, financial, compliance, or production decisions.

Check assumptions against drawings, measurements, current material data, and the applicable design code. Apply required load combinations and safety factors, then obtain qualified review and testing for consequential designs.

• Propeller Thrust

  Axial thrust from ideal momentum change ṁ(vout−vin) through a propeller control volume; excludes pressure thrust.

• Bernoulli Total Head

  Total ideal-flow head as elevation plus pressure head and velocity head; excludes friction and pump terms.

• Extrusion Pressure

  Ideal frictionless extrusion pressure from a supplied mean flow stress times ln(initial area/final area); actual die pressure may be higher.