Skip to main content

Analysis of Pitch and Plunge Effects on Unsteady Airfoil Behavior

Buy Article:

$30.00 plus tax (Refund Policy)

Abstract:

An analysis was conducted into the effects of pitch versus plunge forcing an unsteady airfoil behavior. Experimental measurements of unsteady airloads were analyzed in conjunction with classical unsteady airfoil theory and a semi‐empirical model for dynamic stall. The separate contributions to the unsteady airloads due to angle of attack and pitch rate are shown to be the key variables governing aerodynamic damping, the onset of leading edge separation, and dynamic stall.

Document Type: Research Article

DOI: http://dx.doi.org/10.4050/JAHS.37.69

Affiliations: Ctr. for Rotorcraft Education and Research, Dept. of Aerospace Engineering, University of Maryland, College Park, Md.

Publication date: July 1, 1992

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

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

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

ahs/jahs/1992/00000037/00000003/art00007
dcterms_title,dcterms_description,pub_keyword
6
5
20
40
5

Access Key

Free Content
Free content
New Content
New content
Open Access Content
Open access content
Subscribed Content
Subscribed content
Free Trial Content
Free trial content
Cookie Policy
X
Cookie Policy
ingentaconnect 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