A Modification to Thin-airfoil-section Theory, Applicable to Arbitrary Airfoil Sections, to Account for the Effects of Thickness on the Lift Distribution
David Graham
Jan 1951 · National Advisory Committee for Aeronautics
Ebook
17
Pages
reportRatings and reviews aren’t verified Learn More
About this ebook
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report 833, 1945, has been modified to increase the accuracy of the calculation of the load distribution, due to camber and angle of attack, on airfoil sections of arbitrary camber and thickness. Comparison of theoretical and experimental distributions are presented. The results show that the modification improves the predictions of lift distributions for both angle of attack and camber.
Rate this ebook
Tell us what you think.
Reading information
Smartphones and tablets
Install the Google Play Books app for Android and iPad/iPhone. It syncs automatically with your account and allows you to read online or offline wherever you are.
Laptops and computers
You can listen to audiobooks purchased on Google Play using your computer's web browser.
eReaders and other devices
To read on e-ink devices like Kobo eReaders, you'll need to download a file and transfer it to your device. Follow the detailed Help Center instructions to transfer the files to supported eReaders.
