Three-dimensional LDA in the vortical flow around a lifting delta wing at Mach 2.3

A. L. Heyes; J. T. Turner

doi:10.1117/12.150562

6 August 1993 Three-dimensional LDA in the vortical flow around a lifting delta wing at Mach 2.3

A. L. Heyes, J. T. Turner

Author Affiliations +

Proceedings Volume 2052, Fifth International Conference on Laser Anemometry: Advances and Applications; (1993) https://doi.org/10.1117/12.150562
Event: Laser Anemometry: Advances and Applications: Fifth International Conference, 1993, Koningshof, Veldhoven, Netherlands

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.

Citation Download Citation

A. L. Heyes and J. T. Turner "Three-dimensional LDA in the vortical flow around a lifting delta wing at Mach 2.3", Proc. SPIE 2052, Fifth International Conference on Laser Anemometry: Advances and Applications, (6 August 1993); https://doi.org/10.1117/12.150562

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