a) A convergent-divergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure P, and a constant stagnation temperature To. With the aid of sketches give a clear account of the operation of convergent-divergent nozzles as a function of back pressure P. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. A rocket is equipped with a convergent-divergent nozzle (==3.0). b) supply temperture and pressure Determine the design choked subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the the nozzle is an ideal nozzle. c) Determine the range of pressure ratios () for which a normal shock wave appears in the divergent part of the nozzle. d) At an altitude of 11 km what should be the supply pressure to the nozzle in order to have a fully expanded nozzle. What would be the nozzle's discharge mass flow rate per unit throat area? For this part you may assume that the supply stagnation temperature is 1000 K. The atmospheric pressure and temperature at 11 km altitude are 0.23 bar and 216 K respectively.

a) A convergent-divergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure P, and a constant stagnation temperature To. With the aid of sketches give a clear account of the operation of convergent-divergent nozzles as a function of back pressure P. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. A rocket is equipped with a convergent-divergent nozzle (==3.0). b) supply temperture and pressure Determine the design choked subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the the nozzle is an ideal nozzle. c) Determine the range of pressure ratios () for which a normal shock wave appears in the divergent part of the nozzle. d) At an altitude of 11 km what should be the supply pressure to the nozzle in order to have a fully expanded nozzle. What would be the nozzle's discharge mass flow rate per unit throat area? For this part you may assume that the supply stagnation temperature is 1000 K. The atmospheric pressure and temperature at 11 km altitude are 0.23 bar and 216 K respectively.

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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