solution6

solution6 - 650:460 Aerodynamics Homework Assignment No. 6...

Info iconThis preview shows pages 1–5. Sign up to view the full content.

View Full Document Right Arrow Icon

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: 650:460 Aerodynamics Homework Assignment No. 6 Prof. Doyle Knight Tel: 732 445 4464, Email: doyleknight@gmail.com Office hours: Tues and Thur, 4:30 pm - 6:00 pm and by appointment Fall 2009 1 Problem 7.3 When a GA(W)-1 airfoil section is at an angle of attack of 4 , the lift coefficient is 1.0. Using Eq (7.20), calculate the angle of attack at which a wing whose aspect ratio is 7.5 would have to operate to generate the same lift coefficient. What would the angle of attack have to be to generate this lift coefficient for a wing whose aspect ratio is 6.0 ? Solution The angles of attack are related by 2 = 1 + C L parenleftbigg 1 AR 2- 1 AR 1 parenrightbigg The first wing has AR 1 = and C L = 1 . 0 at 1 = 4 = 0 . 0698 rad. Thus 2 = 0 . 0698 + 1 . parenleftbigg 1 7 . 5- 1 parenrightbigg = 0 . 1123 rad = 6 . 432 2 Problem 7.3 The angle of attack required to generate the same lift coefficient for AR 2 = 6 is 2 = 0 . 0698 + 1 . parenleftbigg 1 6- 1 parenrightbigg = 0 . 1229 rad = 7 . 04 3 Problem 7.4 Consider a planar wing ( i.e. , no geometric twist) which has a...
View Full Document

Page1 / 13

solution6 - 650:460 Aerodynamics Homework Assignment No. 6...

This preview shows document pages 1 - 5. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online