Consider a circular cylinder in a hypersonic flow, with its axisperpendicular to the flow. Let φ be the angle measured between radiidrawn to the leading edge (the stagnation point) and to any arbitrary pointon the cylinder. The pressure coefficient distribution along the cylindricalsurface is given by Cp = 2 cos2 φ for 0 ≤ φ ≤ π/2 and 3π/2 ≤ φ ≤ 2πand Cp = 0 for π/2 ≤ φ ≤ 3π/2. Calculate the drag coefficient for thecylinder, based on projected frontal area of the cylinder.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
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Chapter5: Analysis Of Convection Heat Transfer
Section: Chapter Questions
Problem 5.68P
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Consider a circular cylinder in a hypersonic flow, with its axis
perpendicular to the flow. Let φ be the angle measured between radii
drawn to the leading edge (the stagnation point) and to any arbitrary point
on the cylinder. The pressure coefficient distribution along the cylindrical
surface is given by Cp = 2 cos2 φ for 0φπ/2 and 3π/2 ≤ φ ≤ 2π
and Cp = 0 for π/2 ≤ φ ≤ 3π/2. Calculate the drag coefficient for the
cylinder, based on projected frontal area of the cylinder.

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