Investigation Of Shock Wave Boundary Layer Interaction Under The Effect Of Heating Or Cooling

Shock wave boundary layer interaction is the key factor that limits supersonic and hypersonic vehicle,and the most typical SWBLI exists in inner and outer supersonic and hypersonic flow.In actual flight while the frictional force causes wall temperature changed results in more complicated SWBLI.The experimental study and numerical simulation of shock wave boundary layer interaction have been for decades,while the fundamentals of shock wave boundary layer interaction still unsolved.In this thesis,experimental study and numerical simulation were used to research the change of wall temperature influenced turbulent boundary layer and SWBLI.The experimental study realized by heating/cooling experimental plate.Numerical simulation researched turbulent boundary layer and SWBLI flowfield without the effect of 3D side-wall.In this thesis,the heating experiment group and the cooling experiment group were designed to reseach how different wall temperature influence turbulent boundary layer and SWBLI.This experimental research included non-contact technology like the nanoparticle-based planar laser scattering(NPLS)and supersonic particle image velocimetry(PIV),investigated the basic structures of turbulent boundary layer and the SWBLI flow-field under the effect of heating and cooling.The numerical simulation cooperated with experiments and build simulation model based on experiments.The turbulence model was S-A and application software was Fluent.The boundary layer displacement thickness and the boundary layer momentum thickness under the different wall temperature were analysed and compared to experimental results.The scale of separation in shock wave boundary layer interaction,the distribution of bottom wall static pressure,the distribution of bottom wall skin friction coefficient under the effect of different wall temperature and compared to experimental results.Combined with the result of experimental study and numerical simulation,this thesis discussed the change of turbulent boundary layer and SWBLI caused by different wall temperature.Analysis indicated that different wall temperature influenced thermal expansion then results in changing the nature of boundary layer in further.On the other hand,the viscous of incoming flow was changed when under different wall temperature and resulted in the Reynold number.Further the change of incoming boundary layer resulted in shock wave structure and the other parameters changed in shock wave boundary layer interaction under the same incident shock wave strength.