Department of Aerospace Engineering, University of Glasgow
Abstract
This paper describes and presents results from static wind tunnel tests conducted on a
60° delta wing at a root chord Reynolds number of 2.7 x 10[sup]6. In these tests, the wing
was instrumented with 192 miniature pressure transducers which, in conjunction with
a powerful multi-channel data-logging system, allowed the distribution of timevarying
surface pressures to be measured at high temporal resolution. Analysis
indicates that the distribution of root-mean-square pressure on the leeward surface of
the wing can provide considerable insight into the behaviour of both the primary and
secondary vortex structures. In addition, it has been established that the frequency
content of pressure signals measured in the vicinity of these vortex structures is
sensitive to the vortex state. It is suggested that these data features can be directly
attributed to previously observed behavioural characteristics of the vortex breakdown
process
