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■ Consider a symmetric the aerofoil at an AOA, α. Apply thin aerofoil theory and show that the vorticity distribution is given by, y(0) = 2a√∞ (1+ cos 0) /sin 0 ■ Hence show that the circulation is, 1 And that the lift per unit span is: L= pV_r=2π pVac ■ What is the lift coefficient C/ ? ■ Show that the moment coefficient about the leading edge is: Cm.le = -0.25c₁

■ Consider a symmetric the aerofoil at an AOA, α. Apply thin aerofoil theory and show that the vorticity distribution is given by, y(0) = 2a√∞ (1+ cos 0) /sin 0 ■ Hence show that the circulation is, 1 And that the lift per unit span is: L= pV_r=2π pVac ■ What is the lift coefficient C/ ? ■ Show that the moment coefficient about the leading edge is: Cm.le = -0.25c₁

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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■ Consider a symmetric the aerofoil at an AOA, α. Apply thin aerofoil theory and show that the vorticity distribution is given by, y(0) = 2a√∞ (1+ cos 0) /sin 0 ■ Hence show that the circulation is, 1 And that the lift per unit span is: L= pV_r=2π pVac ■ What is the lift coefficient C/ ? ■ Show that the moment coefficient about the leading edge is: Cm.le = -0.25c₁
Transcribed Image Text:■ Consider a symmetric the aerofoil at an AOA, α. Apply thin aerofoil theory and show that the vorticity distribution is given by, y(0) = 2a√∞ (1+ cos 0) /sin 0 ■ Hence show that the circulation is, 1 And that the lift per unit span is: L= pV_r=2π pVac ■ What is the lift coefficient C/ ? ■ Show that the moment coefficient about the leading edge is: Cm.le = -0.25c₁
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