Question

Consider a flat plate airfoil in supersonic flow. The real drag coefficient should be a sum of wave drag and friction drag: C_D = c_d + C_f, where C_f is the friction drag, which is assumed to be a constant. And C_D = (4α^2)/(√(M_∞^2-1)) for a given freestream Mach number M_∞ > 1.2. Write the expression of lift-to-drag ratio (C_L/C_D), find the value of α when this ratio is maximum, and (C_L/C_D)_max.

Name: consider flat plate airfoil in supersonic flow the real drag coefficient should be a sum of wave drag and friction drag cdcdcf where cfis the friction drag which is assumed as a constant 99514
Uploaded: 2023-07-12T09:13:35-08:00
Duration: 3 min 17 s
Channel: Madhur L
Description: consider flat plate airfoil in supersonic flow the real drag coefficient should be a sum of wave drag and friction drag cdcdcf where cfis the friction drag which is assumed as a constant 99514

          Consider a flat plate airfoil in supersonic flow. The real drag coefficient should be a sum of wave drag and friction drag: C_D = c_d + C_f, where C_f is the friction drag, which is assumed to be a constant. And C_D = (4α^2)/(√(M_∞^2-1)) for a given freestream Mach number M_∞ > 1.2. Write the expression of lift-to-drag ratio (C_L/C_D), find the value of α when this ratio is maximum, and (C_L/C_D)_max.

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University Physics with Modern Physics

Hugh D. Young 14th Edition

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Solved by Expert Madhur L

07/12/2023

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Consider a flat plate airfoil in supersonic flow. The real drag coefficient should be a sum of wave drag and friction drag: C_D = c_d + C_f, where C_f is the friction drag, which is assumed to be a constant. And C_D = (4α^2)/(√(M_∞^2-1)) for a given freestream Mach number M_∞ > 1.2. Write the expression of lift-to-drag ratio (C_L/C_D), find the value of α when this ratio is maximum, and (C_L/C_D)_max.