Engineering Sciences

Propulsion

20th century

Advanced

Rocket Thrust Equation

F = \dot{m} v_e + (P_e - P_a) A_e

Thrust equals mass flow times exhaust velocity plus pressure difference at nozzle exit.

By Various

Engineering Sciences

20th century · Various

Human Reviewed

84%

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Why it matters: Design equation for all chemical and electric rocket engines.

Discoverers: Various (20th century)

What does it mean?

Thrust equals mass flow times exhaust velocity plus pressure difference at nozzle exit.

Why should I care?

Design equation for all chemical and electric rocket engines.

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South — Derivations

Derivation

Variables & Units

Symbol	Name	Unit	Meaning
$F$	Thrust	N	Force
$\dot{m}$	Mass flow	kg/s	Propellant flow rate
$v_e$	Exhaust velocity	—	m/s
$P_e$	Exit pressure	—	Pa

Worked Example

High mass flow and exhaust velocity produce millions of newtons for orbital launch.

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Sources & further reading

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