2 - AE 2020 LOW-SPEED AERODYNAMICS Assignment # 2 Please...

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AE 2020 LOW-SPEED AERODYNAMICS Assignment # 2 Please show your work for credit. Momentum Equation Problems 1) Again, consider steady, compressible flow of air through the turbojet engine shown below. The engine is axisymmetric (i.e. it has a circular cross-section) with a radius of R = 0 . 4m . The aircraft on which this engine is attached is traveling at a speed of sec 140 1 m U = through standard atmosphere at an altitude of 5 km. The exhaust velocity varies as a function of the distance from the centerline of the axisymmetric (i.e. circular cross-section) engine. The exhaust velocity is given by u 2 = u max 1 - r 2 R 2 ( ) where r is the radial coordinate. The density of the exhaust is 3 2 7 . 0 m kg = ρ . Calculate the total force generated by the engine. Does this correspond to thrust or to drag? You must explain your answer for credit. 2) Water flows steadily through a circular pipe around the bend shown in the figure below. Known conditions are
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2 - AE 2020 LOW-SPEED AERODYNAMICS Assignment # 2 Please...

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