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