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A rocket's required mass ratio as a function of effective exhaust velocity ratio. The classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity and can thereby move due to the ...
Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output. TSFC may also be thought of as fuel consumption (grams/second) per unit of thrust (newtons, or N), hence thrust-specific .
distance per vehicle per unit fuel mass; e.g., km/kg. [11] distance per vehicle per unit energy; e.g., miles per gallon equivalent (mpg-e). Energy consumption (reciprocal efficiency) [3] is expressed terms of fuel consumption: [2] volume of fuel (or total energy) consumed per unit distance per vehicle; e.g. l/100 km or MJ/100 km.
In aircraft, loading less than full fuel for shorter trips is standard practice to reduce weight and fuel consumption. ... 1,000 kg (320 km distance suborbital) 12.8
If a force-based unit system is used, impulse is divided by propellant weight (weight is a measure of force), resulting in units of time. The problem with weight, as a measure of quantity, is that it depends on the acceleration applied to the propellant, which is arbitrary with no relation to the design of the engine.
Fuel consumption monitor from a 2006 Honda Airwave.The displayed fuel economy is 18.1 km/L (5.5 L/100 km; 43 mpg ‑US). A Briggs and Stratton Flyer from 1916. Originally an experiment in creating a fuel-saving automobile in the United States, the vehicle weighed only 135 lb (61.2 kg) and was an adaptation of a small gasoline engine originally designed to power a bicycle.
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Take-off can occur when the vehicle's g-force exceeds local gravity (expressed as a multiple of g 0). The thrust-to-weight ratio of rockets typically greatly exceeds that of airbreathing jet engines because the comparatively far greater density of rocket fuel eliminates the need for much engineering materials to pressurize it.