PRESSURE MEASUREMENTS OVER THE TIP REGION OF A RECTANGULAR WING -- PART I. STATIONARY WING

摘要

Measurements of surface pressure in the tip region of a stationary rectangular wing of NACA 0015 profile and semi-aspect ratio of 2 are reported. These measurements have been obtained in several chordwise planes at spanwise locations ranging from the tip to 1.5 chord lengths inboard. The measurements extend over incidences from zero to post-stall angles (up to 30 degrees). The mean pressure data have been used to calculate the lift, drag and pitching moment coefficients as a function of the angle of incidence at several spanwise locations in the tip region. The distinguishing feature of the present experiments is the unique design of the model that allowed the pressure data to be obtained with a very high spatial resolution. The data are thus suitable for the estimation of the pressure gradients in the chordwise and spanwise directions and hence the surface fluxes of the corresponding vorticity components. The pressure measurements over the stationary wing reported in this paper, and those over the oscillating wing reported in a companion paper represent the first phase of an ongoing research project to study the vortex dynamics associated with three-dimensional dynamic stall over the tip region of oscillating rectangular wings.