(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1),V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider thedischarge flow is supersonic and the throat area is 0.1 m² Assume y= 1.4 andR= 287 J/kg.K.High PressureLow VelocityLow PressureHigh VelocityGasesGasesSubsonicSupersonicThroat(1).Convergent Section(2)Divergent SectionFigure 2[Gambarajah 2]Determine the Mach number at section (1).(ii)Determine the stagnation temperature and pressure.(iii) Calculate the pressure, density and velocity at throat area of convergent-divergent nozzle.(iv) Calculate the mass flow rate in kg/s for the flow.

Answered: Image /qna-images/answer/8f302542-1bba-466c-aa84-17b4237fdee9.jpg

(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1), V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the discharge flow is supersonic and the throat area is 0.1 m². Assume y= 1.4 and R= 287 J/kg.K.

(b) The upstream of the isentropic air flow convergent-divergent nozzle at section (1), V=188 m/s, Pr= 130 kPa, and T= 28°C, as shown in Figure 2. Consider the discharge flow is supersonic and the throat area is 0.1 m². Assume y= 1.4 and R= 287 J/kg.K.

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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