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The thrust-to-weight ratio is usually calculated from initial gross weight at sea level on earth [6] and is sometimes called thrust-to-Earth-weight ratio. [7] The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5]
TSFC or SFC for thrust engines (e.g. turbojets, turbofans, ramjets, rockets, etc.) is the mass of fuel needed to provide the net thrust for a given period e.g. lb/(h·lbf) (pounds of fuel per hour-pound of thrust) or g/(s·kN) (grams of fuel per second-kilonewton). Mass of fuel is used, rather than volume (gallons or litres) for the fuel ...
US customary units lbf thrust divided by lb weight is also dimensionless. To convert a 'weight' given in kilograms into a weight in newtons, multiply by 9.806 65 m/s 2. |Power/weight= Power-to-weight ratio (for gas-turbine engines), calculated by dividing engine power by engine weight, kilowatts/kilogram (kW/kg) and shaft horsepower/pound (shp/lb)
In rocketry, a heavier engine with a higher specific impulse may not be as effective in gaining altitude, distance, or velocity as a lighter engine with a lower specific impulse, especially if the latter engine possesses a higher thrust-to-weight ratio. This is a significant reason for most rocket designs having multiple stages.
The radial flow compressor was widely used for early turbojet engines but advantages in performance that came with the axial compressor in terms of pressure ratio, SFC, specific weight and thrust for each square foot of frontal area were presented in 1950 by Hayne Constant [52] However, a radial flow compressor is still the best choice for ...
Thrust: weight ratio [e] Oxidiser: fuel ratio Aeon 1 ... Gas generator [86] 266,893 [87] 70 NewtonFour
For vertical launch of a rocket the initial thrust at liftoff must be more than the weight. Each of the three Space Shuttle Main Engines could produce a thrust of 1.8 meganewton , and each of the Space Shuttle's two Solid Rocket Boosters 14.7 MN (3,300,000 lbf ), together 29.4 MN.
Specific thrust is the thrust per unit air mass flowrate of a jet engine (e.g. turbojet, turbofan, etc.) and can be calculated by the ratio of net thrust/total intake airflow. [ 1 ] Low specific thrust engines tend to be more efficient of propellant (at subsonic speeds), but also have a lower effective exhaust velocity and lower maximum airspeed.