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  2. Thrust - Wikipedia

    en.wikipedia.org/wiki/Thrust

    If the rocket or aircraft is moving at about a constant speed, then distance divided by time is just speed, so power is thrust times speed: [9] = This formula looks very surprising, but it is correct: the propulsive power (or power available [10]) of a jet engine increases with its speed. If the speed is zero, then the propulsive power is zero.

  3. Wind-turbine aerodynamics - Wikipedia

    en.wikipedia.org/wiki/Wind-turbine_aerodynamics

    This maximum coefficient is the Betz limit. Betz was able to show that the maximum coefficient of power of a wind turbine is 16/27. Airflow operating at higher thrust will cause the axial induction factor to rise above the optimum value. Higher thrust causes more air to be deflected away from the turbine.

  4. Propeller theory - Wikipedia

    en.wikipedia.org/wiki/Propeller_theory

    Under certain mathematical premises of the fluid, there can be extracted a mathematical connection between power, radius of the propeller, torque and induced velocity. Friction is not included. The blade element theory (BET) is a mathematical process originally designed by William Froude father of Robert Edmund Froude (1878), David W. Taylor ...

  5. Thrust-to-weight ratio - Wikipedia

    en.wikipedia.org/wiki/Thrust-to-weight_ratio

    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]

  6. Jet engine performance - Wikipedia

    en.wikipedia.org/wiki/Jet_engine_performance

    The kinetic energy is left behind the engine without contributing to the thrust power [26] and is known as residual velocity loss. The thrust force from a stationary engine becomes thrust power when an aircraft is moving under its influence. Zhemchuzhin et al. [27] show an energy balance for a turbojet engine in flight in the form of a Sankey ...

  7. Thrust-specific fuel consumption - Wikipedia

    en.wikipedia.org/wiki/Thrust-specific_fuel...

    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 ...

  8. Range (aeronautics) - Wikipedia

    en.wikipedia.org/wiki/Range_(aeronautics)

    Thrust power is the speed multiplied by the drag, is obtained from the lift-to-drag ratio: =; here Wg is the weight (force in newtons, if W is the mass in kilograms); g is standard gravity (its exact value varies, but it averages 9.81 m/s 2).

  9. Advance ratio - Wikipedia

    en.wikipedia.org/wiki/Advance_ratio

    The advance ratio is critical for determining the efficiency of a propeller. At different advance ratios, the propeller may produce more or less thrust. Engineers use this ratio to optimize the design of the propeller and the engine, ensuring that the vehicle operates efficiently at its intended cruising speed, see propeller theory.