onsider an ideal nozzle of a rocket flying at an altitude where the ambient pressure and mperature are 26.5 kPa and 223 K, respectively. The nozzle is designed to expand air m its combustion chamber in which the pressure and temperature are Po kPa and 1400 respectively to a Mach number of 2.00. The exit area of this nozzle is to be 0.196 m². u may assume the chamber temperature remains constant. 1- Calculate the nozzle supply pressure and throat area, mass flow rate through the nozzle and its thrust when operating at its design condition;
onsider an ideal nozzle of a rocket flying at an altitude where the ambient pressure and mperature are 26.5 kPa and 223 K, respectively. The nozzle is designed to expand air m its combustion chamber in which the pressure and temperature are Po kPa and 1400 respectively to a Mach number of 2.00. The exit area of this nozzle is to be 0.196 m². u may assume the chamber temperature remains constant. 1- Calculate the nozzle supply pressure and throat area, mass flow rate through the nozzle and its thrust when operating at its design condition;
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:Question B3
Consider an ideal nozzle of a rocket flying at an altitude where the ambient pressure and
temperature are 26.5 kPa and 223 K, respectively. The nozzle is designed to expand air
from its combustion chamber in which the pressure and temperature are Po kPa and 1400
K respectively to a Mach number of 2.00. The exit area of this nozzle is to be 0.196 m².
You may assume the chamber temperature remains constant.
1- Calculate the nozzle supply pressure and throat area, mass flow rate through
the nozzle and its thrust when operating at its design condition;
DEN5242 (May 2019)
Question B3 continued
2- Calculate the mass flow rate through the nozzle for a pressure ratio
Po
Ph
of
= 1.005.
3- Calculate the mass flow rate through the nozzle at a chamber pressure of
50 kPa;
4- Determine the chamber pressure at which a normal shock wave stands at the
exit plane of the nozzle.
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