■ 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
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
Related questions
Question
![■ 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](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F255f75c6-e44c-40a5-be9e-1d78604e9303%2Fee7167dc-0beb-429d-a30f-b2dc135d6d62%2Fa4v0008_processed.jpeg&w=3840&q=75)
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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