The temperature of air in a flow is 725°R. Calculate the speed of sound. 2. The temperature in the reservoir of a supersonic wind tunnel is 625°R. In the test section, the flow velocity is 1835 ft/s. Assuming adiabatic flow, what is the Mach Number in the test section? 3. Assume isentropic flow through a supersonic nozzle. The test-section conditions are p = 2.25 atm, T = 205K, and M = 1.65. What are the reservoir pressure and temperature values? 4. A point in a compressible flow has the following properties: T = 245K, V = 275 m/s, and p = 1.85 atm. At this point, calculate the values of po, To, p* , T* , and M* .