Characteristic Velocity
Characteristic velocity, abbreviated as U, measure the effectiveness of the combustion of a rocket engine at high temperature and pressure, seperate from nozzle performance. It is used to compare different propellant and propulsion systems.
Characteristic Velocity formulas
\(\large{ U = \frac { p_c \; A } { \dot m_f } }\) | |
\(\large{ U = \sqrt { 2 \; Ec \; c \; \Delta T } }\) | (Eckert number) |
\(\large{ U = \sqrt { \frac{\Delta p}{Eu \; \rho} } }\) | (Euler number) |
Where:
\(\large{ U }\) = characteristic velocity
\(\large{ A }\) (Greek symbol rho) = area of throat
\(\large{ \rho }\) (Greek symbol rho) = density
\(\large{ Ec }\) = Eckert number
\(\large{ Eu }\) = Euler number
\(\large{ \dot m_f }\) = mass flow rate
\(\large{ \Delta p }\) = pressure differential
\(\large{ p_c }\) = pressure of chamber
\(\large{ c }\) = specific heat
\(\large{ \Delta T }\) = temperature change
Tags: Equations for Velocity