Problem 1 (30 points) with air at Po = 1,000 kPa and To Consider a nozzle system design with two throats as shown in figure 1. Assume that there is a large reservoir downstream of the shock is indicated as station 2. 300 K. The flow experiences a shock at station 1. Immediately (a) What is the pressure, temperature, and density at the first throat (with area A*)? (b) What is the maximum cross sectional area A** that will be needed for the flow to recover to sonic speed (M = 1) at the second throat? (c) What is the total temperature of the flow at the exit of this system (before completely leaving the nozzle system)? Po = 1,000kPa To = 300K A* = 9in shock (1) (2) A** Vacuum A = A2 = 16.2in Figure 1: Problem setup for a double nozzle design.