Help me solve this problem of dynamic gasesChose the correct For unchoked c-d nozzle, the -1supersonic flow through the:diverging part can be attained bydecreasing the exit pressure.increasing the mass flow rate until chockingthe throat.increasing the exit pressure. Oincreasing the exit pressure excessively. OIf you know that the dynamic -2temperature of air is 50 K. Then, itsspeed is23.6 m/s O317 m/s11.83 m/s169.4 m/sMach number at a certain section -3in a diverging part of a c-d nozzle is0.5. At farther section (towards theexit), Mach number reduces to 0.4.Hence, the cross-sectional area ofthe farther section is greater by18.7 % O33.8% O53.2%45.3 %Across the normal shock wave,-4which of the following relations is?validA* x M = constantPo = constant OA* x Po = constantA* x To = constantFor a supersonic flow through a-5converging duct, its speed increases.along the ductFalse OTrue OO O O

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For unchoked c-d nozzle, the -i supersonic flow through the :diverging part can be attained by decreasing the exit pressure. increasing the mass flow rate until chocking the throat. increasing the exit pressure. increasing the exit pressure excessively. O If you know that the dynamic -2 temperature of air is 50 K. Then, its speed is 23.6 m/s 317 m/s 11.83 m/s 169.4 m/s

For unchoked c-d nozzle, the -i supersonic flow through the :diverging part can be attained by decreasing the exit pressure. increasing the mass flow rate until chocking the throat. increasing the exit pressure. increasing the exit pressure excessively. O If you know that the dynamic -2 temperature of air is 50 K. Then, its speed is 23.6 m/s 317 m/s 11.83 m/s 169.4 m/s

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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