**Problem 4.** A converging-diverging nozzle, with a throat area of \( A_t = 10 \, \text{cm}^2 \), is attached to a large tank in which the pressure and temperature are maintained at \( p_0 = 8.0 \, \text{bar} \) and \( T_0 = 350 \, \text{K} \). The nozzle exit area is \( A_e = 14 \, \text{cm}^2 \).(a) For a throat Mach number of \( \bar{M}_{At} = 1 \), determine the exit Mach number corresponding to the following three cases: case I (isentropic subsonic flow, \( M_{aI} \)), case II (isentropic supersonic or "design conditions" flow, \( M_{aII} \)), and case III (flow with a normal shock in the exit plane, \( M_{aIII} \)).(b) Determine the back pressures corresponding to all three cases: \( p_I \), \( p_{II} \), and \( p_{III} \).(c) Sketch the corresponding T-s diagram for all three cases.(d) Briefly discuss how changing the exit area changes the design Mach number.

Data given - At= 10cm2 Ae = 14 cm2 Po = 8 bar = 8×105 Pa To= 350 K r= 1.4

Problem 4. A converging-diverging nozzle, a with throat area of A = 10 cm?, is attached to a large tank in which the pressure and temperature are maintained at Po = 8.0 bar and To = 350 K. The nozzle exit area is A. = 14 cm?. (a) For a throat Mach number of Ma =1 determine the exit Mach number corresponding to the following three cases: case I (isentropic subsonic flow, Maj), case II (isentropic supersonic or "design conditions" flow, Ma1), and case III (flow with a normal shock in the exit plane, Ma). (b) Determine the back pressures corresponding to all three cases: P1. PI, and Pm . (c) Sketch the corresponding T-s diagram for all three cases. (d) Briefly discuss how changing the exit

Problem 4. A converging-diverging nozzle, a with throat area of A = 10 cm?, is attached to a large tank in which the pressure and temperature are maintained at Po = 8.0 bar and To = 350 K. The nozzle exit area is A. = 14 cm?. (a) For a throat Mach number of Ma =1 determine the exit Mach number corresponding to the following three cases: case I (isentropic subsonic flow, Maj), case II (isentropic supersonic or "design conditions" flow, Ma1), and case III (flow with a normal shock in the exit plane, Ma). (b) Determine the back pressures corresponding to all three cases: P1. PI, and Pm . (c) Sketch the corresponding T-s diagram for all three cases. (d) Briefly discuss how changing the exit

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

**Problem 4.** A converging-diverging nozzle, with a throat area of \( A_t = 10 \, \text{cm}^2 \), is attached to a large tank in which the pressure and temperature are maintained at \( p_0 = 8.0 \, \text{bar} \) and \( T_0 = 350 \, \text{K} \). The nozzle exit area is \( A_e = 14 \, \text{cm}^2 \).

(a) For a throat Mach number of \( \bar{M}_{At} = 1 \), determine the exit Mach number corresponding to the following three cases: case I (isentropic subsonic flow, \( M_{aI} \)), case II (isentropic supersonic or "design conditions" flow, \( M_{aII} \)), and case III (flow with a normal shock in the exit plane, \( M_{aIII} \)).

(b) Determine the back pressures corresponding to all three cases: \( p_I \), \( p_{II} \), and \( p_{III} \).

(c) Sketch the corresponding T-s diagram for all three cases.

(d) Briefly discuss how changing the exit area changes the design Mach number.

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