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For example, as the Earth's rotational velocity is 465 m/s at the equator, a rocket launched tangentially from the Earth's equator to the east requires an initial velocity of about 10.735 km/s relative to the moving surface at the point of launch to escape whereas a rocket launched tangentially from the Earth's equator to the west requires an ...
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 ...
"In actual rocket nozzles, the exhaust velocity is not really uniform over the entire exit cross section and such velocity profiles are difficult to measure accurately. A uniform axial velocity, v e, is assumed for all calculations which employ one-dimensional problem descriptions. This effective exhaust velocity represents an average or mass ...
In baseball statistics, exit velocity (EV) is the estimated speed at which a batted ball is travelling as it is coming off the player's bat. Batters generally aim for a higher exit velocity in order to give opposing fielders less time to react and attempt a defensive play; however, many batters are still able to accrue hits without a high exit ...
The proportionality constant varies, and can be solved for a uniform flow, where is the incoming air velocity, is the velocity at the actuator disc, and is the final exit velocity: d m d t = ρ A v {\displaystyle {\frac {\mathrm {d} m}{\mathrm {d} t}}=\rho A{v}}
A space vehicle's flight is determined by application of Newton's second law of motion: =, where F is the vector sum of all forces exerted on the vehicle, m is its current mass, and a is the acceleration vector, the instantaneous rate of change of velocity (v), which in turn is the instantaneous rate of change of displacement.
Characteristic velocity or , or C-star is a measure of the combustion performance of a rocket engine independent of nozzle performance, and is used to compare different propellants and propulsion systems. c* should not be confused with c, which is the effective exhaust velocity related to the specific impulse by: =. Specific impulse and ...
An approximate result for the exit velocity of a projectile having been accelerated by a single-stage coilgun can be obtained by the equation [17] = m being the mass of the projectile, defined as kg V being the volume of the projectile, defined as m 3