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!!