The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing

Abstract

The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.

Theoretical and Computational Investigation on Swept Back Wing using CFD Method

“…Kosinov et.al (2019) studied experimentally and numerically to determine how changes in the mild angle of attack affect the laminar turbulent transition in the swept-wing supersonic boundary layer [10]. Kishi et.al (2019) resolved the design issues using a multi-fidelity approach that included a hybrid surrogate model assisted by evolutionary computation in order to decrease the necessary computation time.…”