New User Special Price Expires in

Let's log you in.

Sign in with Facebook


Don't have a StudySoup account? Create one here!


Create a StudySoup account

Be part of our community, it's free to join!

Sign up with Facebook


Create your account
By creating an account you agree to StudySoup's terms and conditions and privacy policy

Already have a StudySoup account? Login here

Introduction to Aeronautics

by: Kaycee Anderson

Introduction to Aeronautics MAE 3050

Marketplace > Cornell University > Aerospace Engineering > MAE 3050 > Introduction to Aeronautics
Kaycee Anderson
GPA 3.72


Almost Ready


These notes were just uploaded, and will be ready to view shortly.

Purchase these notes here, or revisit this page.

Either way, we'll remind you when they're ready :)

Preview These Notes for FREE

Get a free preview of these Notes, just enter your email below.

Unlock Preview
Unlock Preview

Preview these materials now for free

Why put in your email? Get access to more of this material and other relevant free materials for your school

View Preview

About this Document

Class Notes
25 ?




Popular in Course

Popular in Aerospace Engineering

This 2 page Class Notes was uploaded by Kaycee Anderson on Saturday September 26, 2015. The Class Notes belongs to MAE 3050 at Cornell University taught by Staff in Fall. Since its upload, it has received 96 views. For similar materials see /class/214345/mae-3050-cornell-university in Aerospace Engineering at Cornell University.

Similar to MAE 3050 at Cornell


Reviews for Introduction to Aeronautics


Report this Material


What is Karma?


Karma is the currency of StudySoup.

You can buy or earn more Karma at anytime and redeem it for class notes, study guides, flashcards, and more!

Date Created: 09/26/15
MampAE 305 October 247 2006 Wings with Elliptic Span Loading D A Caughey Sibley School of Mechanical 8 Aerospace Engineeiing Cornell University Ithaca New York 148537501 These notes provide7 as a supplement to our textbook 2 a description of the analysis used to demonstrate the properties of elliptic span loading for Wings of nite span 1 The Elliptical Load Distribution For a Wing With an elliptical spanWise load distribution the sectional lift7 or lift per unit span L as a function of the spanWise coordinate y can be Written mew17 lt1 Where b is the Wing span and Z0 is the maximum sectional lift at the center of the Wing The value of 0 can be related to the Wing lift coef cient by noting that the integral across the span of the section lift is the total lift L7 or 122 2 L 0 1739 dy 2 52 b This integral can be evaluated using the trigonometric substitution cos 9 7 2i 7 3 b Which gives L sin29d9wi 4 2 0 4 Note that this integral could also have been evaluated using the fact that the area of an ellipse is simply 7r times the product of its semiminor Z0 and semimajor 122 axes The lift coef cient is thus given by L Mob 0 7 if L gyms 2pU2S 5 Now7 the downwash velocity taken positive downward is related to the distribution of vor ticity 777 across the span by 1 52 7a wi y if 7 d 7 6 4W 7W 777 y Where the strength of the vortex sheet is related to the spanWise loading by dl 7 1 d 7 M0 77 7 777 CT iipUbQ Wi REFERENCES 2 Thus combining Eqs 5 6 and 7 we can write 2US 52 77 my WCL 2 dn 8 520779 1 Introducing the trigonometric substitution of Eq 3 and correspondingly 277 cos 7 can be written in the form 7 US 7r cosqbdqb 7 7r2b2 CL cosqb 7 cost9 9 The integral appearing here is a standard Glauert integral which can be evaluated from the general formula see eg 7r cos 45 dab sin m9 7 10 0 cosqbicost 7r sint9 This gives the value of the integral appearing in Eq 9 as 7r so we have U 70 7 11 w WAR L where we have introduced the wing aspect ratio AR 1225quot Thus the induced angle of attack is seen for the elliptical span loading to be given by 71 E N CL 678111 UWARi 12 Thus for the elliptical span loading the induced angle of attack is seen to be ll Constant across the span 2 Proportional to the wing lift coefficient and 3 lnversely proportional to the wing aspect ratio AR bQSi Since for the elliptical distribution of lift the induced angle of attack is constant independent of spanwise position the induced drag Di is simply equal to D Lsinei 13 Thus the coef cient of induced drag is given by CZ CD1CLEWA 14 Although not demonstrated here it can also be shown see eg that the elliptical span loading produces the minimum induced drag for a given total lift and wing spani References 1 Li Mi MilneThompson Theoretical Aerodynamics Dover New York 1958 2 Richard S Shevell Fundamentals of Flight Second Edition PrenticeHall New York 1989


Buy Material

Are you sure you want to buy this material for

25 Karma

Buy Material

BOOM! Enjoy Your Free Notes!

We've added these Notes to your profile, click here to view them now.


You're already Subscribed!

Looks like you've already subscribed to StudySoup, you won't need to purchase another subscription to get this material. To access this material simply click 'View Full Document'

Why people love StudySoup

Steve Martinelli UC Los Angeles

"There's no way I would have passed my Organic Chemistry class this semester without the notes and study guides I got from StudySoup."

Kyle Maynard Purdue

"When you're taking detailed notes and trying to help everyone else out in the class, it really helps you learn and understand the I made $280 on my first study guide!"

Jim McGreen Ohio University

"Knowing I can count on the Elite Notetaker in my class allows me to focus on what the professor is saying instead of just scribbling notes the whole time and falling behind."


"Their 'Elite Notetakers' are making over $1,200/month in sales by creating high quality content that helps their classmates in a time of need."

Become an Elite Notetaker and start selling your notes online!

Refund Policy


All subscriptions to StudySoup are paid in full at the time of subscribing. To change your credit card information or to cancel your subscription, go to "Edit Settings". All credit card information will be available there. If you should decide to cancel your subscription, it will continue to be valid until the next payment period, as all payments for the current period were made in advance. For special circumstances, please email


StudySoup has more than 1 million course-specific study resources to help students study smarter. If you’re having trouble finding what you’re looking for, our customer support team can help you find what you need! Feel free to contact them here:

Recurring Subscriptions: If you have canceled your recurring subscription on the day of renewal and have not downloaded any documents, you may request a refund by submitting an email to

Satisfaction Guarantee: If you’re not satisfied with your subscription, you can contact us for further help. Contact must be made within 3 business days of your subscription purchase and your refund request will be subject for review.

Please Note: Refunds can never be provided more than 30 days after the initial purchase date regardless of your activity on the site.