Experimental study of hypersonic boundary layer transition on a flat plate delta wing
| Autor: | Shiyong Yao, Lei Wang, Yang Pan, Duan Yi, Xiaoli Zhao, Changwan Min |
|---|---|
| Rok vydání: | 2020 |
| Předmět: |
Fluid Flow and Transfer Processes
Physics Hypersonic speed Delta wing Angle of attack Mechanical Engineering General Chemical Engineering Aerospace Engineering Reynolds number Mechanics Vortex Physics::Fluid Dynamics symbols.namesake Boundary layer Nuclear Energy and Engineering Mach number symbols Wind tunnel |
| Zdroj: | Experimental Thermal and Fluid Science. 112:109990 |
| ISSN: | 0894-1777 |
| DOI: | 10.1016/j.expthermflusci.2019.109990 |
| Popis: | The boundary layer transition on a flat plate delta wing was investigated in the Mach 6 quiet wind tunnel via global temperature and wall pressure measurements as well as flow visualization. The results show that the boundary layer transition on side line is earlier than that on center line, and larger angle of attack promotes the boundary layer transition. As the Reynolds number increases, the transition position of boundary layer moves upstream. The hot streaks on the center line of delta wing at 0° angle of attack which are symmetrically distributed with respect to the center line at 10° angle of attack are suspected to be arised from the vortical flow rather than the boundary layer transition. High frequency disturbances occurring nonlinear phase coupling transfer the energy to low frequency structures, and finally the low frequency large scale structures induce to boundary layer transition. The intensity of nonlinear interaction prior to boundary layer transition is stronger than that in turbulent boundary layer. In addition, the unstable region of disturbance waves depends on the Reynolds number. |
| Databáze: | OpenAIRE |
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