-Pipe A 21 Pipe B 11110 Question 1 Two pipes, made from the same material, are connected to a water tank (p= 10³ kg/m³, u = 10-³ Pa-s). The level H is constant. Pipe A has a length L and diameter D, and pipe B has a length 2L and diameter D. Both pipes discharge to the atmosphere. You may neglect minor losses but not major losses. The gravity cannot be neglected. Assume steady-state and no friction in the tank. (a) Which pipe will pass the larger flow rate if the flow is ideal without friction? Justify your answer with equations but without numerical calculations. (b) Which pipe will pass the larger flow rate if the flow is fully turbulent with fA=fB = constant? Justify your answer with equations but without numerical calculations. (c) Which pipe will pass the larger flow rate if the flow is laminar? Justify your answer with equations but without numerical calculations.

In some of Joule’s experiments (Figure 1), work was done on water held in an adiabatic calorimeter. The work was done by a rotating paddle, driven by falling weights. Assume the volume of the water remains constant during these experiments.a. In one experiment a 25-kg mass was allowed to fall 20 times through a height of 2 m; what was the maximum amount of work done? b. If a 25-kg mass were fired into the calorimeter and brought to a standstill, what should its initial velocity be to accomplish the same effect as in (a)? c. If the calorimeter held 1.2 kg of water and if process (a) caused the water temperature to rise from 288 to 290 K, what is the numerical value for the factor that connects temperature rise to work under these conditions?

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Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm? and an exit area of 20 cm?. The reservoir conditions are P. = 300 kPa and To = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.