The Study Of Supersonic Axisymmetric Shock Wave Boundary Layer Interaction

The phenomenon of Shock Wave Boundary Layer Interaction(SWBLI) which widely exists in the supersonic/hypersonic vehicle and the scramjet inlet can induce unsteady large-scale separation, even lead to unstart of the inlet. In order to enhance the whole performance and the application value of the vehicle, it is necessary to ensure that the inlet could start and retain well capability in wide range of Mach numble. For the past sixty years, the phenomenon of SWBLI was studied widely by experts and academician who majored in fluid dynamicsThe inlet owning axisymmetric distributing is regarded as the research background, and axisymmetric SWBLI is studied through numerical calculation and experiment in this paper. S-A single turbulent model is choosed after comparing the different turbulent model result in computing separation flow field. A nanoparticle-based planar laser-scattering(NPLS) technique and supersonic particle image velocity(PIV) technique are used in the experiment of this article. In this paper, the law of axisymmetric SWBLI separation along with radius and the flow field structure of cone boundary and axisymmetric SWBLI are focused.A model which forecasts the separation of SWBLI at a certain Reynold Numble was acquired through a large amount of numerical calculation result.Equal intensity axial converging shock wave was acquired by use of planar curve shock wave conversed designing method, the parameters near shock wave incidence position could be stay the same by making use of parallelogram method. When R /?1, axisymmetric flow can be approximately thought as two dimension flow, axisymmetric separation point model and separation length model have no relation with radius. When1 ? R /? ?100, the gene A in the separation point model increases with radius, and reach an asymptotic-plateau value, the length of separation decreases with radius, and can be fitted by a two rank polynomial.High spatiotemporal resolution votex structures in the cone turbulent boundary layer were captured by the NPLS technique, and the velocity field was analyzed with the PIV technique. Large scale turbulent structures and stripe structures were found in the cone turbulent boundary layer NPLS images. At leeward section the height of boundary layer vortices structures away from the wall largens quickly along with the increase of attack angle in the range of small attack angles, when the attack angle becomes bigger, it increases slowly; the boundary layer vortices structures of the leeward section are pulled intensely. Through analyzing the axisymmetric SWBLI flow field’s NPLS and PIV images, obvious differences were found comparing two dimension SWBLI. The shape and the waves structures depend on the boundary layer characteristic near shock wave incidence position.