Hostname: page-component-cb9f654ff-mwwwr Total loading time: 0 Render date: 2025-08-17T14:52:52.589Z Has data issue: false hasContentIssue false
  • English
  • Français

Pressure measurements on a half delta wingoscillating in pitch

Published online by Cambridge University Press:  04 July 2016

J. P. Vaughan  and
N. J. Wood
J. P. Vaughan
Affiliation:
School of Mechanical Engineering, University of Bath, Bath, UK
N. J. Wood
Affiliation:
School of Mechanical Engineering, University of Bath, Bath, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

A rigid, 55° sweep, half delta wing has been oscillatedin pitch at subsonic speeds, and the unsteadypressures on both the upper and lower surfacesrecorded for pre-stalled conditions. Theoscillations were of low amplitude and atfrequencies equivalent to a typical wing firstbending mode for full scale applications.

When compared to a quasi-steady approximation, theunsteady pressures on the upper surface of the winglag the steady case along the line of the primaryattachment. The lag represents a constant convectivetime from the leading-edge with increasing frequencyof oscillation. A further localised area of laggingflow is observed beneath the vortex burst point, thelocation of which is a function of mean angle ofattack.

The magnitude of the unsteady pressure variations wasseen to increase linearly with the amplitude of thepitching oscillation while the phase lag was seen toincrease linearly with frequency parameter.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 990 , December 1995 , pp. 432 - 438
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. Pilkington, D.J. and Wood, N.J. Unsteady aerodynamic effects of trailing edge controls on delta wings, ICAS-94-10.1.1, 19th conference of the International Council of the Aeronautical Sciences, Anaheim, 1994.Google Scholar
2. Soltani, M.R. and Bragg, M.B. Measurements on an oscillating 70- Deg delta wing in subsonic flow, J Aircr, 1990, 27, (3), pp 211–217.Google Scholar
3. Huyer, S.A., Robinson, M.C. and Luttges, M.W. Unsteady aerodynamic loading produced by a sinusoidally oscillating wing, J Aircr, 1992, 29, (3), pp 366–373.Google Scholar
4. Lemay, S.P., Batill, S.M. and Nelson, R.C. Vortex dynamics on a pitching delta wing, J Aircr, 1990, 27, (2), pp 131–138.Google Scholar
5. Greenwell, D.I. and Wood, N.J. Some observations on the dynamic response of the vortex burst phenomenon to wing motion, Aeronaut J, February 1994, 98, (972), pp 49–59.Google Scholar
6. Forsching, H.W. Unsteady aerodynamic forces on an oscillating wing at high incidences and flow separation, AGARD-CP-483, Aircraft loads due to flow separation, paper No 7, 1990.Google Scholar
7. Van der Bliek, J.A. Notes on half model testing in windtunnels, AGARD report 259, 1959.Google Scholar