Skip to main content
padlock icon - secure page this page is secure

Finite Difference Modeling of Rotor Flows Including Wake Effects

Buy Article:

$35.00 + tax (Refund Policy)

This paper gives a brief consideration of rotary wing finite difference methods. The main concerns are the means to properly account for the effect of the wake on the blade. Examples are given of an approach where wake effects are introduced by specifying an equivalent angle of attack. An alternate approach is also given where discrete vortices are introduced into the finite difference grid. The resulting computations of hovering and high‐advance‐ratio cases compare well with experiment. Some consideration is also given to the modeling of low‐to‐moderate advance‐ratio flows.
No Reference information available - sign in for access.
No Citation information available - sign in for access.
No Supplementary Data.
No Article Media
No Metrics

Document Type: Research Article

Affiliations: U.S. Army Aeromechanics Laboratory, AVSCOM, Ames Research Center, Moffett Field, Calif.

Publication date: April 1, 1984

More about this publication?
  • The Journal of the AHS is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by The Vertical Flight Society and presents innovative papers covering the state-of-the-art in all disciplines of VTOL design, research and development. (Please note that VFS members receive significant discounts on articles and subscriptions.)

    Journal subscribers who are VFS members log in here if you are not already logged in.

    Authors can find submission guidelines and related information on the VFS website.

  • Access Key
  • Free content
  • Partial Free content
  • New content
  • Open access content
  • Partial Open access content
  • Subscribed content
  • Partial Subscribed content
  • Free trial content
Cookie Policy
X
Cookie Policy
Ingenta Connect website makes use of cookies so as to keep track of data that you have filled in. I am Happy with this Find out more