How would the equation look if instead of knowing the
effective exhaust velocity we knew the force the exhaust was exerting on the rocket.
The equation is:
[tex] \Delta V = v_e * ln(\dfrac{m_0}{m_1}) [/tex]
would [tex] \Delta V [/tex] still be proportional to the log of the initial mass over the final mass?
http://en.wikipedia.org/wiki/Tsiolko...ocket_equation