Problem 2. A small rocket motor, that uses hydrogen and oxygen for the fuel, is operated in a testing chamber on a thrust stand at a simulated altitude of z = 10 km. The measured chamber stagnation temperature is To = 1500 K and gage pressure is Po,gage = 8.0 MPa (defined relative to the absolute pressure in the chamber). The combustion product is water vapor, which may be treated as an ideal gas with constant specific heat ratio of k = 1.30. Expansion of the exhaust occurs through a converging-diverging nozzle with design Mach number of Ma. = 3.5 and exit area of A. = 7.0 cm?. (a) Evaluate the pressure at the nozzle exit plane. (b) Calculate the mass flow rate of exhaust gas. (c) Determine the force exerted by the rocket motor on the thrust stand. (d) Sketch the T-s diagram for the combustion gasses from stagnation conditions to the chamber.

Problem 2. A small rocket motor, that uses hydrogen and oxygen for the fuel, is operated in a testing chamber on a thrust stand at a simulated altitude of z = 10 km. The measured chamber stagnation temperature is To = 1500 K and gage pressure is Po,gage = 8.0 MPa (defined relative to the absolute pressure in the chamber). The combustion product is water vapor, which may be treated as an ideal gas with constant specific heat ratio of k = 1.30. Expansion of the exhaust occurs through a converging-diverging nozzle with design Mach number of Ma. = 3.5 and exit area of A. = 7.0 cm?. (a) Evaluate the pressure at the nozzle exit plane. (b) Calculate the mass flow rate of exhaust gas. (c) Determine the force exerted by the rocket motor on the thrust stand. (d) Sketch the T-s diagram for the combustion gasses from stagnation conditions to the chamber.

Name: **Problem 2.** A small rocket motor, that uses hydrogen and oxygen fo
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Description: **Problem 2.** A small rocket motor, that uses hydrogen and oxygen for the fuel, is operated in a testing chamber on a thrust stand at a simulated altitude of \( z = 10 \, \text{km} \). The measured chamber stagnation temperature is \( T_0 = 1500 \,

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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**Problem 2.** A small rocket motor, that uses hydrogen and oxygen for the fuel, is operated in a testing chamber on a thrust stand at a simulated altitude of \( z = 10 \, \text{km} \). The measured chamber stagnation temperature is \( T_0 = 1500 \, \text{K} \) and gage pressure is \( p_{0,\text{gage}} = 8.0 \, \text{MPa} \) (defined relative to the absolute pressure in the chamber). The combustion product is water vapor, which may be treated as an ideal gas with constant specific heat ratio of \( k = 1.30 \). Expansion of the exhaust occurs through a converging-diverging nozzle with design Mach number of \( M_{A_e} = 3.5 \) and exit area of \( A_e = 7.0 \, \text{cm}^2 \).

(a) Evaluate the pressure at the nozzle exit plane.

(b) Calculate the mass flow rate of exhaust gas.

(c) Determine the force exerted by the rocket motor on the thrust stand.

(d) Sketch the T-s diagram for the combustion gasses from stagnation conditions to the chamber.

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