Question 2) In order to test a jet engine at sea level, it is aimed to design a static thrust stand for the given following conditions: Inlet: Velocity= 200 m/s, Area= 1.2 m², Static absolute pressure= 75 kPa, Static temperature= 272 K Exit: Velocity= 600 m/s, Static gage pressure= 0 kPa a) Using the control volume in the figure to the right, calculate the nominal thrust level to design this stand for. b) Rewrite the equation of conservation of momentum if another control volume is selected for the analysis as shown to the right. Show how it simplifies down to the equation you have used in part (a). Explain why. c) In which direction would the engine move if it was not mounted onto the thrust stand?
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Problem 1 The forces on an aircraft flying at altitude are shown in the picture. An F35 fighter jet has a mass m = 14,000 kg and its engines are capable of a maximum thrust T_MAX = 190,000 N. (a) At a cruising speed of 250 m/s the air drag is 40,000 N. What is the maximum forward acceleration that the F35 can achieve? (b) This aircraft's wings have a total cross-sectional area of 43 m^2. What is the pressure difference between the upper and lower side of the wings required for the aircraft to fly at constant altitude? (Hint: the vertical forces must cancel.)
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