Physics for Scientists and Engineers
Physics for Scientists and Engineers
6th Edition
ISBN: 9781429281843
Author: Tipler
Publisher: MAC HIGHER
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Chapter 13, Problem 15P
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The aircraft fuselage can be approximated as a circular cylinder for non-viscous aerodynamicanalysis. Given that the surface velocity of inviscid flow around a circular cylinder is:V = 2U∞sinθWhere q = 0 is a point on the axis of symmetry, show that the maximum dynamic pressure on thecylinder amounts to: 2 ρU∞2If P∞ at some distance upstream of the cylinder is 100kPa, and U∞ is 50m/s, determine the minimumstatic pressure on the cylinder surface for an air flow with density 1.225kg/m3
Water flows at a rate of 0.035 m3/s in a horizontal pipe whose diameter is reduced from 15 cm to 8 cm by a reducer. If the pressure at the centerline is measured to be 480 kPa and 445 kPa before and after the reducer, respectively, determine the irreversible head loss in the reducer. Take the kinetic energy correction factors to be 1.05.
Consider an airfoil in a flow at standard sea level conditions with a freestream velocity of 50 m/s. At a given point on the airfoil, the pressure is 0.9 × 105 N/m2. Calculate the velocity at this point.

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