Need help finding the thrust and exit diameter of a rocket

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SUMMARY

The discussion focuses on calculating the thrust and exit diameter of a small rocket powered by high-pressure nitrogen, with specific parameters including a throat diameter of 1.0 inch, operating pressure of 120 psi, and a temperature of 510R. The thrust equation used is F = m dot * Ve + (pe - p0) * Ae, where the user is advised to calculate the exit area using the provided equation A/A*=(1/M^2)((2/gamma+1)(1+(gamma-1/2)M^2))^(gamma+1/gamma-1). The user also seeks to compare thrust and exit diameters at exit Mach numbers of 5.0 and 7.0, indicating a need for precise calculations based on the given conditions.

PREREQUISITES
  • Understanding of rocket propulsion principles
  • Familiarity with thermodynamics, specifically the ideal gas laws
  • Knowledge of fluid dynamics, particularly compressible flow
  • Proficiency in using thrust equations and area calculations in rocket design
NEXT STEPS
  • Research the calculation of exit area in rocket nozzles using compressible flow equations
  • Study the effects of varying Mach numbers on thrust and exit diameter
  • Explore the implications of operating pressures and temperatures on rocket performance
  • Learn about the specific impulse and efficiency of high-pressure nitrogen propulsion systems
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Aerospace engineers, rocket propulsion specialists, and students studying fluid dynamics and thermodynamics in rocket design will benefit from this discussion.

strine07
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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!
 
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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.
 

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