MAE2_Solution1

MAE2_Solution1 - altitude of 10,000 m. Calculate the...

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MAE 2 Homework #1 (Fall 2010) Note: Some numbers and wording may be changed relative to the textbook problems. When differences occur, this assignment sheet has precedence. Problem 2.3 Calculate the weight of air (in Newtons) contained within a room 6 m long, 5 m wide, and 3 m high. Assume atmospheric pressure and temperature of 1.01x10 5 N/m 2 and 15 o C, respectfully. Problem 3.1 At 12 km in the standard atmosphere, the pressure, density, and temperature are 1.9399x10 4 N/m 2 , 3.1194x10 -1 kg/m 3 , and 216.66 K, respectively. Assuming an isothermal region, calculate the standard atmospheric values of pressure, density, and temperature at an altitude of 18 km. Check your work by also reporting values from the standard atmosphere tables (Appendix A). Problem 3.4 Consider an airplane flying at a pressure altitude of 10,200 m and a density
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Unformatted text preview: altitude of 10,000 m. Calculate the outside air temperature (in Kelvin). Problem 4.4 A venturi tube is a converging-diverging nozzle that was used to measure airspeed before 1930. Subscript 1 represents the inlet conditions and subscript 2 denotes conditions at the throat. The measured pressure difference is p 1- p 2 = 80 lb/ft 2 , and the area ratio is A 2 /A 1 = 0.30. What is the inlet velocity, V 1 , assuming the airplane is flying at standard sea level? Problem 4.31 Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 440 o F, respectively. If the Mach number at the nozzle exit is 3.0, calculate the exit pressure, temperature, and density....
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MAE2_Solution1 - altitude of 10,000 m. Calculate the...

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