Complex Theoretical and Experimental Investigations of Flow Structure Near V-Shaped Wings

Abstract

For estimating the supersonic flow near the V-shaped wings, the method and programs based on the Euler and Navier-Stokes equations were developed. The calculation results are compared with the experimental data obtained in the aerodynamic tunnel with the help of the unique optical direct-shadow method of the supersonic space gas flow visualization via the laser technology. As for the nonviscous flow, the vortex structures appear as the result of the Mach interaction of shock waves with the formation of the contact discontinuity of the certain intensity. When dealing with the viscous flow, the vortex structure appearance is based on the viscous layer formation near the surface of the object under the influence of the pressure fall or the pressure gradient in the external flow field. The comparison of the calculation results and experimental data revealed the vortex structures with the nonviscous and viscous origin. The chapter contains the examples of the calculations based on different programs to show the both possibility and impossibility to get the right solution using different mathematical models of the flow.