Q5. Air with stagnation conditions of 35 bar and 450 K enters a combustion duct via a converging-divergingnozzle with area ratio of 4 as shown. Heat is added to the duct. At the end of the duct there is a normalshock, after which the static temperature is found to be 560 K.(a) Draw a T-s diagram for the system.(b) Find the Mach number after the shock.P.(c) Determine the amount of heat added in the duct.ToPage 2 of 2 pagesFigure Q5

given data; ⇒air at stagnation condition;⇒stagnation pressure(P0)=35bar⇒stagnation…

Answered: QS. Air with stagnation conditions of…

Elements Of Electromagnetics

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Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Q5. Air with stagnation conditions of 35 bar and 450 K enters a combustion duct via a converging-diverging nozzle with area ratio of 4 as shown. Heat is added to the duct. At the end of the duct there is a normal shock, after which the static temperature is found to be 560 K. (a) Draw a T-s diagram for the system. (b) Find the Mach number after the shock. P. (c) Determine the amount of heat added in the duct. T. Figure Q5
Q1- A converging nozzle with a throat area of 0.001² m is operated with air at aback pressure of 5.91 bars. The nozzle is fed from a large plenum chamber where the stagnation pressure and the temperature are 10 bars and 60 °C, respectively. The exit Mach number and mass flow rate are to be determined.
2) Prove that the mass of gases (m) flowing in the convergent-divergent nozzle of an afterburning jet engine is expressed by 7 Po :A 1 im _7+1_ (1+4M²)VR/To Where Po, To are the total pressure and temperature at a nozzle section having an area of A For chocking conditions,, the Mach number is unity at throat section (Ath), and the above relation is reduced to 20-1) Y Po Ath VR/To
b. Air flows in a converging-diverging nozzle from stagnation conditions at P, = 500 kPa and T. = 400 K as shown in Fig.2. The exit Throat To static pressure is 450 kPa, and the throat ME Po and exit areas are 0.01 m? and 0.015 m2 Po respectively. Assuming isentropic flow, Supersonie nozzle Ag determine the Mach number, ME at exit and the mass flow rate th when the flow is supersonic in the divergence section of the PE (Ma, = 1) duct. (Take for air, K=1.4, and R= 287 m?/s?.K) Fiq.2
Q1/2. Air flow isentropically through a supersonic convergent divergent nozzle with 0.6 kg/s. At the inlet, the pressure is 700 kPa and the temperature is 300 K, and the area is 7 cm. If the exit area is 14 cm? calculate: a- The stagnation pressure and temperature. b- The exit Mach number. c- The exit pressure and temperature. d- The area and velocity at the throat. e- What will be the maximum rate of flow and the corresponding exit Mach number if the flow completely subsonic in the nozzle?
The discharge air from a convergent-divergent nozzle at a Mach number of 1.72. The exit pressure is 15 psia, and the temperature is 155 degree F. For isentropic expansion and a negligible inlet velocity, calculate the stagnation pressure, psia.A. 72.31 B. 74.31 C. 76.31 D. 78.31
A turbojet engine with a convergent divergent nozzle expands the flow such that Po = 0.8 P, The engine has the following data at a flight Mach number of 1.5 : Te = 7.5 ,Tt4=1400 K, e. = et = 0.9 , y = 1.34 ,CP; = 1135 J/kg.K If the jet velocity is 1025 m/s, determine the flight altitude.
6. A normal shock occurs at the inlet of a diffuser. The Mach number at the exit of the diffuser is 0.3 and the area ratio between the inlet and outlet of the diffuser is 0.695. Find the Mach number of air at inlet to the diffuser. [Ans. M; = M = 2.64] %3!
Q.1. Air flow adiabatically in a constant area duct. At the inlet of the duct, the Mach number, pressure and temperature are 0.6, 150 kPa and 300 K respectively. Assuming a duct length of 0.45 m, a duct diameter of 0.03 m and a friction coefficient of 0.003, determine the Mach number, temperature, and pressure at the duct outlet. Also, calculate the mass flow rate.
1. From the data given below, calculate the power required to drive the compressor and stage air angles for an axial flow compressor. Stagnation temperature at the inlet: Overall pressure ratio: Isentropic efficiency of the compressor: Mean blade speed: Axial velocity: 288 K 4 0:88 170 m/s 120 m/s Degree of reaction: 0:5 A. P = 439.5 kW, B, = 77.8°, B, = 72.69° C. P = 639.5 kW, B, = 77.8°, B2 = -72.69° B. P = 539.5 kW, B, = -77.8°, B2 = 72.69° D. P = 739.5 kW, B, = -77.8°, B2 = -72.69°
D5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic flow at the outlet with no shacks inside the nozzle. Determine the mach number and static pressure at the outlet if the area of the outlet is 0.900 m2, the area of the throat is 0.490m2, and the stagnation pressure is 215 kPa.
Air at a stagnation temperature and pressure of 201 K and 6.895 x 105 N/m2, respectively, flows from a reservoir through a converging nozzle that exhausts into an atmosphere where the pressure is 1.014 x 105 N/m2. Calculate: a) the pressure in the nozzle exit plane, b) the minimum stagnation pressure for which the flow is chocked, c) the exit plane pressure if the stagnation pressure is reduced to 1.724 x 105 N/m2.

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