Consider the following NACA airfoils: 2412, 23012, 23021 a. For each of these airfoils, find the L/D ratio for angle of attack of 0, 4, 8 and 12 b. For each airfoil find the angle of maximum L/D and find the stall angle c. Find which airfoil will provide the maximum lift for any given geometry and flow conditions

Elements Of Electromagnetics
7th Edition
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Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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Consider the following NACA airfoils:
2412, 23012, 23021
a. For each of these airfoils, find the L/D ratio for angle of attack of 0, 4, 8 and 12
b. For each airfoil find the angle of maximum L/D and find the stall angle
c. Find which airfoil will provide the maximum lift for any given geometry and flow
conditions
Transcribed Image Text:Consider the following NACA airfoils: 2412, 23012, 23021 a. For each of these airfoils, find the L/D ratio for angle of attack of 0, 4, 8 and 12 b. For each airfoil find the angle of maximum L/D and find the stall angle c. Find which airfoil will provide the maximum lift for any given geometry and flow conditions
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