compressible Aerodynamics

please answer all parts

Problem 2 (2 points) A convergent-divergent nozzle with AexiA* = 4.0, A* = 1 m, operates under the following conditions with reservoir pressure pres pores 2.2 atm, reservoir temperature Tres = 500 K, and pexit - 1 atm. 2.1 You can verify by calculating the reservoir pressure for shock at the nozzle exit and the reservoir pressure for chocked subsonic flow that a shock occurs in the nozzle. Calculate the location of the shock when Texit = 490.25K. 2.2 Calculate the thrust produced by this nozzle for the design condition of perfectly expanded flow and for chocked subsonic flow