Consider a flat plate at an angle of attack in a viscous supersonic flow; i.e.,there is both skin friction drag and wave drag on the plate. Use lineartheory for the lift and wave-drag coefficients. Denote the total skin frictiondrag coefficient by C f , and assume that it does not change with angle ofattack. (a) Derive the expression for the angle of attack at which maximumlift-to-drag ratio occurs as a function of C f and freestream Mach number.(b) Derive the expression for the maximum lift-to-drag ratio as a functionof C f and freestream Mach number M.

Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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Consider a flat plate at an angle of attack in a viscous supersonic flow; i.e.,
there is both skin friction drag and wave drag on the plate. Use linear
theory for the lift and wave-drag coefficients. Denote the total skin friction
drag coefficient by C f , and assume that it does not change with angle of
attack. (a) Derive the expression for the angle of attack at which maximum
lift-to-drag ratio occurs as a function of C f and freestream Mach number.
(b) Derive the expression for the maximum lift-to-drag ratio as a function
of C f and freestream Mach number M.

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