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Pressure measurements on a half delta wing oscillating 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
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Abstract

A rigid, 55° sweep, half delta wing has been oscillated in pitch at subsonic speeds, and the unsteady pressures on both the upper and lower surfaces recorded for pre-stalled conditions. The oscillations were of low amplitude and at frequencies equivalent to a typical wing first bending mode for full scale applications.

When compared to a quasi-steady approximation, the unsteady pressures on the upper surface of the wing lag the steady case along the line of the primary attachment. The lag represents a constant convective time from the leading-edge with increasing frequency of oscillation. A further localised area of lagging flow is observed beneath the vortex burst point, the location of which is a function of mean angle of attack.

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

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 990 , December 1995 , pp. 432 - 438
Copyright
Copyright © Royal Aeronautical Society 1995 

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