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practicecq_2

# practicecq_2 - 16.540 Internal Flows Spring 2006 Practice...

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16.540 - Internal Flows Spring 2006 Practice Concept Quiz #2 1. [Used as Concept Quiz #3 (2004)] We have seen that whether a flow is rotational or not can have a major difference on its behavior. Below are some examples of situations encountered in fluids engineering. State whether the flow at the downstream station, station 1, is or is not rotational. If it is rotational, indicate the sense of the vorticity. As previously, one to several sentences explaining your reasoning, bolstered by equations and/or a sketch if you think appropriate, are needed for full credit. You can assume that the flow at the station can be approximated as inviscid, i.e. that the effect of wall boundary layers on the overall velocity distribution does not need to be included in your response. a) Fluid flows through a two-dimensional bent duct. The velocity at a station midway through the bend is uniform across the duct. The Mach number is everywhere small compared to unity. Station 1 is in a straight duct downstream of the bend. b) Fluid flows through a screen that covers half the area in a constant area duct, as in the figure below. The screen is normal to the duct wall. The Mach number is everywhere small compared to unity. c) Heat is added to the upper half of the stream in a constant area, two-dimensional, duct. The temperature of the heated fluid that exits the region of heat addition is ten times the (uniform) upstream temperature. The Mach number is everywhere small compared to unity. Station 1 is downstream of the region of heat addition. d) Fluid flows through a straight oblique shock that spans across an inlet. The flow upstream of the shock is uniform. Station 1 is downstream of the shock. e) A compressor stage (a rotor and a stator) has non-uniform work addition, with the work added to the flow increasing from the hub to the tip (i.e., from the inner boundary of the annulus to the outer casing). The flow entering the stage is uniform and axial and the flow leaving the stage is axial. The flow through the stage can be considered isentropic and the Mach numbers are everywhere small compared to unity. Station 1 is downstream of the stage.

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