Volume 7, 2015Progress in Flight Physics – Volume 7
|Page(s)||585 - 604|
|Section||Stability and transition|
|Published online||08 June 2015|
Experimental methods of the study of vortex structures excited by point injection at the leading edge of the oblique wing
Khristianovich Institute of Theoretical and Applied Mechanics Siberian Branch of the Russian Academy of Sciences 4/1 Institutskaya Str., Novosibirsk 630000, Russia
The paper presents the results of application of thermoanemometry on a curved surface and the liquid crystal thermography (LCT) to study the stability of the flow at the leading edge of an oblique wing. Quantitative results of the distribution of the velocity perturbation in the boundary layer near the attachment line were obtained with the help of thermoanemometry. A decrease of boundary-layer stability because of modification of its structure by stationary vortex is found. The method of LCT allowed to expand the study area to 70° on both sides of the attachment line, to get pictures of disturbed flow visualization for multiple modes of injection, and to show the influence of the injection velocity on the size and trajectory of stationary disturbances induced by air jet. Visualization results are consistent with the thermoanemometry.
© Owned by the authors, published by EDP Sciences, 2015