Skip to main content

An Analysis of the Stall Flutter Instability of Helicopter Rotor Blades

Buy Article:

$30.00 plus tax (Refund Policy)


An analytical study was carried out to determine the susceptibility of helicopter rotor blades to a stall flutter instability. This analysis was based on the use of unsteady aerodynamic data previously obtained by the United Aircraft Research Laboratories for the Sikorsky Aircraft Division on an NACA 0012 airfoil oscillating in pitch about its quarter‐chord over a wide range of values of incidence angle, oscillatory frequency, amplitude of motion and free‐stream velocity. It was found that under certain conditions of forward speed and high disk loading, a helicopter rotor blade could encounter regions of negative aerodynamic damping while operating as a retreating blade. The extent of the negative damping regime was sensitive to changes in incidence angle distribution, and for the cases considered herein could produce a maximum of two cycles of unstable torsional motion per revolution. However, under most operating conditions the rotor blade was found to be quite stable. Generally good agreement was found to exist between the results of the present study and those of other investigators at all stages in the development; e.g., the two‐dimensional damping data were in good agreement with the results of Halfman, et al and the final three‐dimensional damping variation with azimuth over the rotor disk was in qualitatively good agreement with the recent work of Ham and Young.

Document Type: Research Article


Affiliations: Aeroelastics Group, Aerophysics Section, United Aircraft Research Laboratories, East Hartford, Connecticut

Publication date: 1967-10-01

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.

  • Access Key
  • Free ContentFree content
  • Partial Free ContentPartial Free content
  • New ContentNew content
  • Open Access ContentOpen access content
  • Partial Open Access ContentPartial Open access content
  • Subscribed ContentSubscribed content
  • Partial Subscribed ContentPartial Subscribed content
  • Free Trial ContentFree trial content
Cookie Policy
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