- #1
strine07
- 4
- 0
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!
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!