Advertisement

Experimental Investigation of Wing Rock of Slender Wings and Aircraft Configurations

  • Robert C. Nelson
  • Andrew S. ArenaJr.
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Abstract

Experimental investigations of the wing rock characteristics of a slender delta wing with 80° sweep, and a 2.5% model of an F-18 are summarized. The studies were conducted in order to identify physical mechanisms responsible for wing rock of slender wings and aircraft configurations. Results obtained on the slender delta wing indicate that wing rock is sustained by a time lag in vortex position, and limited in amplitude by the unsteady behavior of vortex strength. Vortex breakdown has been shown not to be a primary mechanism in wing rock, however its appearance was shown to reduce the steady state amplitude of the motion. The results obtained on the F-18 subscale model agree with those obtained on the full scale flight vehicle. Flow and motion characteristics observed on the F-18 model are consistent with those seen on the slender wing.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Ross, A. J., “Investigation of Nonlinear Motion Experienced on a Slender-Wing Research Aircraft”, Journal of Aircraft, Vol. 9, No. 9, September 1972.CrossRefGoogle Scholar
  2. 2.
    Ross, A. J., “Flying Aeroplanes in Buffet”, Aeronautical Journal, Vol. 81, October 1977.Google Scholar
  3. 3.
    Ross, A. J., and Nguyen, L. T., “Some Observations Regarding Wing Rock Oscillations at High Angles of Attack”, AIAA-88–4371-CP, August, 1988.Google Scholar
  4. 4.
    Chambers, J. R. and Anglin, E. L., “Analysis of Lateral-Directional Stability Characteristics of a Twin-Jet Fighter Airplane at High Angles of Attack”, NASA TN D-5361, August 1969.Google Scholar
  5. 5.
    Arena, Jr., A. S. and Nelson, R. C., “The Effect of Asymmetric Vortex Wake Characteristics on a Slender Delta Wing Undergoing Wing Rock Motion”, AIAA-89–3348, August 1989.Google Scholar
  6. 6.
    Arena, Jr., A. S., Nelson, R. C., and Schiff, L. B., “An Experimental Study of the Nonlinear Dynamic Phenomenon Known as Wing Rock”, AIAA-90–2812, August, 1990.Google Scholar
  7. 2.
    Arena, Jr., A. S., and Nelson, R. C., “Unsteady Surface Pressure Measurements on a Slender Delta Wing Undergoing Limit Cycle Wing Rock”, AIAA-91–0434, January, 1991.Google Scholar
  8. 8.
    Arena, Jr. A. S., “An Experimental and Computational Investigation of Slender Wings Undergoing Wing Rock”, PhD Dissertation, University of Notre Dame, April 1992.Google Scholar
  9. 9.
    Arena Jr., A.S., and Nelson, R.C.,“ A Discrete Vortex Model for Predicting Wing Rock of Slender Wings”, AIAA 92–4497, August, 1992.Google Scholar
  10. 10.
    Fisher, D. F. and Del Frate, J. H., “In-Flight Flow Visualization Characteristics of the NASA F-18 High Alpha Research Vehicle at High Angles of Attack”, SAE Technical Paper Series No. 892222, September 1989.Google Scholar
  11. 11.
    Quast, T., “A Study of High Alpha Dynamics and Flow Visualization for a 2.5% Model of the F-18 HARV Undergoing Wing Rock”, MS Thesis, University of Notre Dame, April, 1991.Google Scholar
  12. 12.
    Quast, T., Nelson, R. C., and Fisher, D. F., “A Study of High Alpha Dynamics and Flow Visualization for a 2.5% Model of the F-18 HARV Undergoing Wing Rock”, AIAA-91–3267, September, 1991.Google Scholar
  13. 13.
    Nelson, R. C., Arena Jr., A. S., and Williams, D. L., “ The Use of Subscale Models to Predict Self-Induced Oscillations of Flight Vehicles”, AIAA Paper 93–0093, January 1993.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1993

Authors and Affiliations

  • Robert C. Nelson
    • 1
  • Andrew S. ArenaJr.
    • 1
  1. 1.Hessert Center for Aerospace Research Department of Aerospace and Mechanical EngineeringUniversity of Notre DameNotre DameUSA

Personalised recommendations