help me solve part i please

6. Consider a supersonic flow through a convergent-divergent nozzle with an exit-to-throat ratio of A, /A* = 5.9 and the throat area is A* = 9.39 in\". The flow is expanded isentropically to supersonic speed at the nozzle exit and the reservoir pressure and temperature are po = 6.2 atm and Ty = 556 R. Using this information and details from Example 10.1, 10.2, and 10.4, along with Problems 10.1 and 10.4, make the following calculations. Assume a specific heat ratio of y = 1.4. Points are indicated next to each Part. a. b. C. Calculate the nozzle exit pressure (p-) in lb/ft'. (2 Points) Calculate the nozzle exit temperature (7) in degrees Rankin (R). (2 Points) Calculate the reservoir density (9) nozzle exit density (p) in slug/ft'. Hint: Remember the equation of state. (2 Points per Part) Calculate the local speed of sound at the nozzle exit (ae) in miles per hour (mi/hr). (3 Points) e. Calculate the flow velocity at nozzle exit (ue) in miles per hour (#i/hr). (2 Points) Calculate the density in the throat (p*) in slug/ff?. Note: Because the flow is sonic through the throat, use Appendix A for the density ratio (3 Points) Calculate the throat temperature (7*) in degrees Rankin (R). Note: Because the flow is sonic through the throat, use Appendix A for the temperature ratio. (2 Points) Calculate the local speed of sound (a*) and velocity (%*) in the throat, in miles per hour (mi/hr). (2 Points per Part) Calculate the mass flow (7) through the Nozzle in slug/s. (2 Points)