3. An air stream, which is traveling at a Mach number of 1.8, undergoes a normal shock wave. The stagnation pressure and temperature before the normal shock wave are 150 kPa and 350 K, respectively. Determine a) the temperature and the pressure after the normal shock wave, b) the Mach number and the velocity after the normal shock wave and c) the stagnation temperature and pressure after the shock wave and d) the entropy change across the normal shock wave (Ans. a) 325.4 K, 94.3 kPa, b) 0.6165, 223 m/s, c) 350 K, 122.2 kPa, d) 59.55 J/kgK)

1.) While the pressure remains constant at 100 psia the volume of a system of air changes from20 ft3to 10 ft3. What are (a) ∆U in Btu, (b) Q in Btu, (c) Wn, Btu2.) Four pounds of air gain 0.491 Btu/R of entropy during a nonflow isothermal process. If p1= 120 psia and V2 = 42.5 ft3find (a) V1 and T1 (b) Q, and (c) Ws with υ1 = 100 ft/sec and υ2 =500 ft/sec.3.) A 1 hp stirring motor is supplied to a tank containing 22.7 kg of air. The stirring action isapplied for 2 hours and the tank losses 850 kJ/hr of heat. Calculate (a) the paddle work inkJ, (b) change of internal in kJ, and (c) the change in temperature of air after 2 hours,assuming that the process occurs at constant volume.4.) A gas with cp = 5.2 kJ/kg.K and R = 2.056 kJ/kg.K initially at 2000 kPa, 3m3and 115oCundergoes an isentropic process to 105 kPa. Find (a) V2 and T2. What is the work (b) if theprocess is nonflow, (c) if the process is steady flow with ΔKE = 10 kJ?

4. It is important to remember that the isentropic relations and normal shock relationsare monotonic with Mach number and can be inverted. To illustrate this, consider thefollowing problems,(a) Given a total temperature to static temperature ratio of 4, determine the Machnumber.(b) If the entropy rises by ∆s/R = 1.0 across a shock, determine the pre- and post-shock Mach numbers and the static pressure jump (p2/p1).

b) Define the definition of sonic flow, supersonic flow, and hypersonic flow.