Abstract: This paper describes an experimental study in which the LDA technique has been applied to investigate the supersonic vortical flow generated by a lifting delta wing at a free stream Mach number of 2.3. A three color system was employed to measure the complex three-dimensional flow field around the delta. The data have been transposed onto a convenient grid and presented as velocity vector and vorticity information so that the effect of changing the angle of incidence is revealed. The results are in good agreement with previous findings from flow visualization and theoretical studies.!5
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