Question B3The engine of an aeroplane is equipped with an ideal convergent nozzle with an area ratioAinlet2.035 ( -A-2.035), as in Figure Q-B3. The aeroplane is flying at an altitude of 11Aexitkm where the atmospheric pressure and temperature are 0.23 bar and 216Krespectively.You may assume the combustion gases entering the nozzle have the same property as air(i.e. y=1.40, R=287 J/kgK and Cp-1004.5J/kgK).Page 6Question B3 continuedinletexitAmles/Aexit -AVAJ-2.035Figure Q-B3a) If the nozzle operates at its critical condition, calculate: the inlet Mach number M;.nozzle's exit velocity V, the inlet stagnation pressure Por- the inlet static pressureFGThe stagnationAjP, and the nozzle's gross thrust per unit exit areatemperature of the gases entering the nozzle is To1200 K.b) If the stagnation pressure at the inlet of the nozzle is reduced to 80% of its value inpart (a), determine the exit static temperature 7;, the nozzle's gross thrust per unitexit area FG. The stagnation temperature remains the same as in part (a) above.c) If the stagnation pressure at the inlet of the nozzle is increased to 120% of its valuein part (a), determine the exit static temperature 7,. the nozzle's gross thrust per

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Question B3 The engine of an aeroplane is equipped with an ideal convergent nozzle with an area ratio 2.035 (inlet-4-2.035), as in Figure Q-B3. The aeroplane is flying at an altitude of 11 Aexit km where the atmospheric pressure and temperature are 0.23 bar and 216K respectively. You may assume the combustion gases entering the nozzle have the same property as air (i.e. y=1.40, R=287J/kgK and Cp 1004.5J/kgK). Page 6 Question B3 continued inlet exit 3 Amlet Aexit -AVAJ-2.035 Figure Q-B3 a) If the nozzle operates at its critical condition, calculate: the inlet Mach number M₁. nozzle's exit velocity , the inlet stagnation pressure Poi. the inlet static pressure FG The stagnation P, and the nozzle's gross thrust per unit exit area temperature of the gases entering the nozzle is Tol-1200 K. b) If the stagnation pressure at the inlet of the nozzle is reduced to 80% of its value in (a), determine the exit static temperature 7;, the nozzle's gross thrust per unit exit area FG. The stagnation temperature remains the same as in part (a) above. c) If the stagnation pressure at the inlet of the nozzle is increased to 120% of its value in part (a), determine the exit static temperature T,. the nozzle's gross thrust per

Question B3 The engine of an aeroplane is equipped with an ideal convergent nozzle with an area ratio 2.035 (inlet-4-2.035), as in Figure Q-B3. The aeroplane is flying at an altitude of 11 Aexit km where the atmospheric pressure and temperature are 0.23 bar and 216K respectively. You may assume the combustion gases entering the nozzle have the same property as air (i.e. y=1.40, R=287J/kgK and Cp 1004.5J/kgK). Page 6 Question B3 continued inlet exit 3 Amlet Aexit -AVAJ-2.035 Figure Q-B3 a) If the nozzle operates at its critical condition, calculate: the inlet Mach number M₁. nozzle's exit velocity , the inlet stagnation pressure Poi. the inlet static pressure FG The stagnation P, and the nozzle's gross thrust per unit exit area temperature of the gases entering the nozzle is Tol-1200 K. b) If the stagnation pressure at the inlet of the nozzle is reduced to 80% of its value in (a), determine the exit static temperature 7;, the nozzle's gross thrust per unit exit area FG. The stagnation temperature remains the same as in part (a) above. c) If the stagnation pressure at the inlet of the nozzle is increased to 120% of its value in part (a), determine the exit static temperature T,. the nozzle's gross thrust per

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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