Volume 7, 2015Progress in Flight Physics – Volume 7
|Page(s)||549 - 568|
|Section||Stability and transition|
|Published online||08 June 2015|
Effect of the local wall cooling/heating on the hypersonic boundary layer stability and transition
Khristianovich Institute of Theoretical and Applied Mechanics Siberian Branch of the Russian Academy of Sciences 4/1 Institutskaya Str., Novosibirsk 630000, Russia
Hypersonic boundary layer stability and transition were studied experimentally and numerically for the test case of 7 degree half-angle cone equipped with local wall heating and cooling. The experiments were performed for M = 6. Heat flux distributions and wall pressure pulsations were measured. It was obtained that variation of the wall temperature significantly affects the transition location. It was found that development of the second mode depends on the upstream wall temperature. The results of numerical simulation confirmed the general trends of the second mode evolution obtained in the experiment.
© Owned by the authors, published by EDP Sciences, 2015