hw_2.pdf

# hw_2.pdf - AerE 411 Homework 2(8 points Figures are...

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1 AerE 411, Homework 2 (8 points) Figures are required for those HW solutions which have figures To receive credit for computer solutions, you must include the source code Note: this document is subject to change by the instructor during the semester. 1. (2 points) Oates . Chapter 2: 2.8. Note : this is the most difficult problem of the homework set. 2. (1 point) Consider the model of a combustion chamber given in class ǒ m . air ) m . fuel Ǔ h t2 * m . air h t1 + m . fuel h The mass flow rate of air through the burner is 800 kg/s. The total temperature of the air enterĆ ing the burner is 500K. The fuel has a heating value of 43,000 kJ/kg and is being burned at a fuel mass flow rate of 8 kg/s. Assuming that the combustion chamber can be modeled as a constant area heat addition, what is the total temperature and total pressure ratio across the burner (i.e. t b + T t2 ń T t1 and p b + P t2 ń P t1 ) and the downstream Mach number, as a function of upstream Mach number. Assume that the upstream Mach number is subsonic in the range 0 to 0.4. Note: you may assume that R + 287 Nm ń kgK , g + 1.4 , and c p + 1004.9 J ń kgK .

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• Spring '14

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