Need help finding the thrust and exit diameter of a rocket

[strine07]

A small rocket powered by high-pressure nitrogen (R = 1776 ft-lb/slug/R, gamma=1.4) is used as an attitude control device. In space, the thrust of a rocket is given by T =mVe
in lbf. Find the thrust and exit diameter of this rocket with a throat diameter of 1.0 inch if it
operates at PT = 120 psi and TT = 510R with M = 3.0 at the exit. Then compare the
thrust and exit diameters when the exit Mach number is 5.0 and 7.0.

*I know I need to use the equation A/A*=(1/M^2)((2/gamma+1)(1+(gamma-1/2)M^2))^(gamma+1/gamma-1) but I'm having trouble finding the appropriate values.

ps sorry if this post is in the wrong area, I'm pretty new to this site!

 

[Vadar2012]

You've got everything you need, except for this part. The thrust equation is:

F = m dot * Ve + (pe - p0) * Ae

Calculate the exit area from the equation you listed. You've been given everything else. Or just look up the old tables.