A supersonic converging-diverging nozzle has an exit-to-throat area ratio of 1.555. The flow at the outside of the nozzle is observed to make an 8° deflection inward. The back pressure is known to be 100 kPa. (a) Determine the Mach number and the static pressure at the exit of the nozzle. (b) Determine the angle of the first oblique shock and the Mach number downstream from the first oblique shock. (c) A second oblique shock turns the flow back in parallel with the jet axis; determine the angle of the second oblique shock. (d) Determine the Mach number and the static pressure in region C. A B C
A supersonic converging-diverging nozzle has an exit-to-throat area ratio of 1.555. The flow at the outside of the nozzle is observed to make an 8° deflection inward. The back pressure is known to be 100 kPa. (a) Determine the Mach number and the static pressure at the exit of the nozzle. (b) Determine the angle of the first oblique shock and the Mach number downstream from the first oblique shock. (c) A second oblique shock turns the flow back in parallel with the jet axis; determine the angle of the second oblique shock. (d) Determine the Mach number and the static pressure in region C. A B C
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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Transcribed Image Text:A supersonic converging-diverging nozzle has an exit-to-throat area ratio of 1.555. The flow at
the outside of the nozzle is observed to make an 8° deflection inward. The back pressure is
known to be 100 kPa.
(a) Determine the Mach number and the static pressure at the exit of the nozzle.
(b) Determine the angle of the first oblique shock and the Mach number downstream from the
first oblique shock.
(c)
A second oblique shock turns the flow back in parallel with the jet axis; determine the angle
of the second oblique shock.
(d) Determine the Mach number and the static pressure in region C.
A
B
C
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