Loose Leaf for Fundamentals of Aerodynamics
Loose Leaf for Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259683992
Author: Anderson, John
Publisher: McGraw-Hill Education
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Chapter 12, Problem 12.6P

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. Answers: (a) α = ( C f ) 1 / 2 ( M 2 1 ) 1 / 4 / 2 ; (b) ( c l / c d ) max = ( c f ) 1 / 2 ( M 2 1 ) 1 / 4

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