Calculate mechanical, aerodynamic, and momentum thrust from fluid mass flow rate, exhaust velocity, and pressure differential.
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A thrust calculator evaluates the total reaction force generated by a propulsion system according to Newton third law of motion. Thrust is produced by accelerating a mass of working fluid (air, water, or combustion gases) through a propeller, nozzle, turbine, or fan duct.
F_{\text{thrust}} = \dot{m} (v_e - v_0) + (p_e - p_0) A_eWhere m-dot is fluid mass flow rate (kg/s), v_e is exit velocity, v_0 is freestream vehicle velocity, p_e is nozzle exit pressure, p_0 is ambient atmospheric pressure, and A_e is exhaust area.
Scenario: An engine expelling 12 kg/s of air at 250 m/s with zero vehicle forward velocity.
Mass Flow Rate: 12 kg/s.
Exit Velocity: 250 m/s.
Static Momentum Thrust: 12 × 250 = 3,000 N (3.0 kN or ~674 lbf).
The international standard unit of thrust is the Newton (N). In imperial units, thrust is expressed in pounds-force (lbf). In hobby RC and drone applications, it is commonly quoted in grams or kilograms of thrust.
Gross thrust is the total momentum generated at the exhaust nozzle. Net thrust subtracts the "ram drag" (the momentum of air entering the intake at the vehicle flight speed).
Multiply Newtons by 0.224809 (or divide by 4.44822). For example, 1,000 N of thrust equals approximately 224.8 lbf.
No. Classical propulsion requires conservation of momentum: to propel a vehicle forward, mass must be accelerated in the opposite direction.
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