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.
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.
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter5: Analysis Of Convection Heat Transfer
Section: Chapter Questions
Problem 5.68P
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Question
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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