Page 2 mechanics and thermodynamics of propulsion

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"Mechanics and Thermodynamics of Propulsion". Addison-Wesley Publishing Company, Inc., USA. ISBN 0-201-14659-2. Each question carry 10 points each, in total 40 points for the assignment. Second chapter helps you to refresh the basic knowledge in thermodynamics and fluid mechanics. The dead line to submit the assignment is 14 th April 2009 before 16:00. You can hand in your assignment at my office, room number L322 located near HPT Kitchen (first floor), call using phone at the entrance with number 7682 to get in. Page 3
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ROCKET PROPULSION Page 8
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HOME ASSIGNMENT 2 (Chapter 11) 1. Using a propellant of molecular weight 15 and flame temperature 3300 K, determine the rocket throat and exhaust areas required for a thrust of 500 kN and an ideal specific impulse of 300 sec. The ambient pressure is 0.1 MPa, and the specific-heat ratio of the propellant is 1.4. How much thrust would this rocket develop id the ambient pressure were changed to 0.03 MPa? How much thrust would be developed by a rocket designed to expand to 0.03 MPa if it had the same stagnation conditions, throat area, and the propellant? (Problem 4, page 560). 2. A rocket thrust chamber has been designed for a chamber pressure P o of 2.0 MPa and “correct” expansion at 10-km altitude where the ambient pressure is 26.5 kPa. The chamber has to be tested at sea level with the design value of the chamber pressure but with back pressure nearly four times the design value. Is it likely that a shock wave will enter the nozzle under test conditions? At what back pressure could a plane normal shock stand in the end plane of the nozzle? Let = 1.4. (Problem 9, page 562) γ 3. A liquid-propellant combustion chamber is 1 m long and 0.3 m in diameter. The temperature and pressure in the chamber are uniform at approximately 3200 K and 15 MPa, and the diameter Reynolds number of the flow through the chamber is of the order of 10 7 . The chamber wall is type 301 stainless steel 2.5 mm thick and is maintained at 110 K on the outside surface. Radiation is one-third the total heat flux. What would be the steady-state inner surface temperature? Use the following data: Page 9
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Conductivity of stainless steel 26 W/m. K, Conductivity of chamber gases 0.17 W/m. K, Prandtl number for chamber gases 0.7. (Problem 13, page 563) INSTRUCTIONS: All the question numbers, page numbers correspond to book Hill, P. and Peterson, R. 1992.
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