Hostname: page-component-7b7567c8c-2n9c9 Total loading time: 0 Render date: 2026-11-15T12:59:56.817Z Has data issue: false hasContentIssue false
  • English
  • Français

Collectively variable incidence wingtipsfor lift control and reduced gustsensitivity

Published online by Cambridge University Press:  04 July 2016

R.H. Barnard
R.H. Barnard*
Affiliation:
Division of Mechanical and Aeronautical Engineering, University of Hertfordshire
Get accessRights & Permissions [Opens in a new window]

Abstract

This paper describes an investigation of theaerodynamic characteristics of collectively variableincidence wing tips at low speeds. Theoreticalconsiderations supported by experimentalmeasurements suggest that the use of articulatedtips which can be rotated to a high incidence forlow speed flight will decrease sensitivity to gusts.Furthermore, windtunnel measurements demonstratethat the use of very high tip incidences can producean increment in maximum overall lift coefficient forsome wing configurations. Another featureinvestigated is the possibility of utilising thelift increment for the purposes of direct liftcontrol. The use of a radio controlled model to testthe practical viability of the concept isdescribed.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 981 , January 1995, pp. 29 - 35
Copyright
Copyright © Royal Aeronautical Society 1995 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1. Knight, M and Bamber, M.J. Windtunnel tests on a model of a monoplane wing with floating ailerons, NACA TN 316, 1929.Google Scholar
2. Weick, F.E. and Harris, T.A. Wind-tunnel research comparing lateral control devices, particularly at high angles of attack, XI Various floating tip ailerons on both rectangular and tapered wings, NACA TN 458, 1933.Google Scholar
3. Soule, H.A. and Gracey, W. A flight comparison of conventional ailerons on a rectangular wing and of conventional and floating wingtip ailerons on a tapered wing. NACA Rep No 630, 1937.Google Scholar
4. Haoermann, J.R. and O'hare, W.M. Investigation of extensible wingtip ailerons on an untapered semispan wing at 0° and 45° sweepback, NACA RM L9H04, 1949.Google Scholar
5. Fischel, J. and Watson, J.M. Low-speed investigation of deflectable wingtip aileron on an untapered 45° sweepback semispan wing with and without endplate, NACA RM No L9J28, 1949.Google Scholar
6. Eney, J.A. and Greenhalgh, S. Low-speed wind-tunnel test of jet flaps and floating wing-tip ailerons on a fighter wing, Naval Air Development Center Rep. No. NADC-74198-30, 1974.Google Scholar
7. White, R.J. Improving airplane efficiency by use of wing maneuver load alleviation, J Aircr, October 1971, 8, (10), pp 769–775.Google Scholar
8. Winter, H. Flow phenomena on plates and aerofoils of short span, NACA TM 798, 1936.Google Scholar
9. Estimation of sideforce, yawing moment and rolling moment derivatives due to rate of roll for complete aircraft at subsonic speeds, Engineering Sciences Data Unit, Data sheet No. 85010, ESDU, London.Google Scholar