By H. Daneshyar
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4) at a stagnation pressure of 140 kN/m 2. It discharges into an atmosphere of static pressure 100 kN/m 2. Show that there is a normal shock in the duct. Find the stagnation pressure of the gas at exit from the nozzle, the Mach numbers immediately upstream and downstream of the shock, and the ratio of the area at the location of the shock to the throat area. Normal shock Solution: I H i i . Z Fig. 5. '. 64 Therefore for subsonic exit (point a, Fig. 0938 too low e 0 Therefore there is a normal shock between the throat and the exit plane.
This can be arranged if the area of the second P throat can be varied. 2 Jet engine intakes Supersonic diffusers are also used for the inlet of jet engines operating at supersonic speeds. These engines usually reach their operating speed by being accelerated from lower speeds (as distinct from overshooting the operating speed) and, as for the supersonic wind tunnel diffuser, operation of the inlet during starting must be investigated. Consider a convergent-divergent inlet having an inlet area AI and throat area AT (Fig.
The flow is adiabatic and reversible. (a) Calculate the maximum possible reduction in area, and the following quantities for that minimum area: Stagnation pressure, stagnation temperature, static pressure, static temperature, velocity and Mach number. (b) At a point where the area is 15% smaller than the initial area, calculate the quantities listed in (a). 5 kN/m 2 , 240 K, 311 m/s, 1. Answer: (a) (b) 2. 566. A jet propelled air liner flies at 15,000 m and at 265 m/s. What is the stagnation pressure and stagnation temperature of the air entering the engine?
