How can I use the Newton Method to find the eccentric anomaly for Mars?

[smmSTV]

So I'm in need of some more help for my astronomy class again.
My professor wants us to write a program that outputs a table with the distance of Mars from the sun (r) and it's true anomaly. The problem is that i need to compute the Eccentric Anomaly (E) from the Mean Anomaly (M). Kepler's equation is E = M + εsin(E), but I can't get it down in terms of E. Seeing as how I'm using c++, it is kind of a necessity. One website seemed to have an equation involving Einitial and Efinals, but it didn't do me any good. Is the idea to set the original Einitial equal to 0 at t=0 (the perihelion point) and find E final in terms of that? At the end of each iteration (I'm running a while loop) the Eintial of the next iteration would be set to the Efinal of the current loop. Anybody got any ideas? Thanks

 

[Philosophaie]

The correct equation is $$M = E - e*sin(E)$$

Solve using the Newton Method:

$$E_{n+1} = E_{n} - \frac{f(E)}{f'(E)}$$
where f(E) = E - e * sin(E) - M
and f'(E) = 1 - e * cos(E)

Loop the above equations until:
$$\frac{f(E)}{f'(E)} < 0.00001$$Or some substantially low number not zero.

Also,$$r = \frac{a * (1 - e ^ 2)}{(1 + e * cos(TA))}$$
where TA - True Anomaly
and a - Semi-Major Axis of Mars