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a rocket stage. The limit depends on the fueled-to-dry mass ratio and on the effective exhaust velocity of the engine. This relation is given by the classical rocket equation:
: where:
: is delta-v of the vehicle (change of velocity plus losses due to gravity and atmospheric drag);
: is the initial total (wet) mass, equal to final (dry) mass plus propellant;
: is the final (dry) mass, after the propellant

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