Design a 1D compressed air rocket engine. Assume standard atm conditions and isentropic flow. k=1.4, R=0.287
Determine:
1. Tank ressure required producing a Machof 1,3,5, 7, and 9.
2. A throat area of 0.5m^2 and a tank stagnation temp of 1000K, determine mass flow rates for each of the design Mach numbers.
3.The final nozzle area for each Mach number
4. The exit temperatures for all Mach numbers.
5. The exit velocity for all Mach nmbers
6. The amount of mass required for each mach number to achieve a burn time of 30 secs, 1 minute, 5 min, 10 min.
7. Size of tank which can hold the required mass of air for each burn time (Volume).
8. The total force generated by the rocket engine for each speed.