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Transitional flow over isolated roughness at hypersonic speed:an infrared thermography study

叶青青  Ferry F.J.Schrijer  Fulvio Scarano  
【摘要】:Boundary layer transition is an important physical process in the design of hypersonic flight vehicles due to its large impact on the aerodynamics and aerothermodynamic process.For a given flight regime,the surface heat flux in the turbulent regime may be up to three times higher than that of a laminar boundary layer leading to higher heat loads to be tolerated by the thermal protection system(TPS).Therefore,in order to further optimize the TPS,an accurate method to predict boundary layer transition is required.When a large roughness element is present in the boundary layer,the transition mechanism is greatly modified,leading to the acceleration of the transition process.In the present research,the transitional flow features over and downstream of isolated roughness elements in hypersonic flow are investigated by means of infrared thermography.The local heat flux distribution in the wake of the roughness element reveals the footprint of multiple streamwise counterrotating vortex pairs.The formation of a turbulent wedge with the spanwise spreading of the wake in the downstream region indicates the early stage of transition and breakdown to turbulence.The onset location of transition is predicted by detecting the origin of the turbulent wedge.Strong dependence of the transition process on the roughness geometry is observed,with significant variations of the lateral spreading rate in the turbulent wedge.Instead,for the present flow conditions negligible variations are associated to changes in Re_h.

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