# Exhaust Velocity

### Some articles on velocity, exhaust velocity, exhaust:

Spacecraft Propulsion - Methods - Reaction Engines - Delta-v and Propellant
... line in free space would produce a net velocity change to the vehicle this number is termed 'delta-v' ... If the exhaust velocity is constant then the total of a vehicle can be calculated using the rocket equation, where M is the mass of propellant, P is the mass of the payload (including the rocket structure), and is ... If the rocket has a payload of mass P, the spacecraft needs to change its velocity by, and the rocket engine has exhaust velocity ve, then the mass M of reaction ...
Mass Ratio - Derivation
... from the Tsiolkovsky's rocket equation where Δv is the desired change in the rocket's velocity ve is the effective exhaust velocity (see specific impulse ... This equation indicates that a Δv of times the exhaust velocity requires a mass ratio of ... a vehicle to achieve a of 2.5 times its exhaust velocity would require a mass ratio of (approximately 12.2) ...
Reaction Engine - Energy Use - Propulsive Efficiency
... energy amounting to (where M is the mass of propellent expended and is the exhaust velocity), which is simply the energy to accelerate the exhaust ... the vehicle - some of it, indeed usually most of it, ends up as kinetic energy of the exhaust ... This comes to an exhaust velocity of about ⅔ of the mission delta-v (see the energy computed from the rocket equation) ...
Project Orion (nuclear Propulsion) - Basic Principles
... The Orion nuclear pulse drive combines a very high exhaust velocity, from 12 to 19 mi/s (19 to 31 km/s) in typical interplanetary designs, with meganewtons of thrust ... For any rocket propulsion, since the kinetic energy of exhaust goes up with velocity squared (kinetic energy = ½ mv2), whereas the momentum and thrust goes up with velocity linearly (mo ... inversely proportional to Isp if power going into exhaust is constant or at its limit from heat dissipation needs or other engineering constraints) ...
Rocket Propellant - Mixture Ratio
... The theoretical exhaust velocity of a given propellant chemistry is a function of the energy released per unit of propellant mass (specific energy) ... is that fuel-rich mixtures have lower molecular weight exhaust, which by reducing increases the ratio which is approximately equal to the theoretical exhaust velocity ... Fuel-rich mixtures actually have lower theoretical exhaust velocities, because decreases as fast or faster than ...

### Famous quotes containing the word exhaust:

Fear can supplant our real problems only to the extent—unwilling either to assimilate or to exhaust it—we perpetuate it within ourselves like a temptation and enthrone it at the very heart of our solitude.
E.M. Cioran (b. 1911)