The interaction between longitudinal vortices and flat plate boundary layer has been studied numerically for both laminar and turbulent flow situations.The vortices are assumed to be placed in an otherwise two-dimensi...The interaction between longitudinal vortices and flat plate boundary layer has been studied numerically for both laminar and turbulent flow situations.The vortices are assumed to be placed in an otherwise two-dimensional boundary layer flow.The flow is assumed to be incompressible and steady.Consid- ering the fact that the velocity,vorticity and temperature gradients in the transverse directions are much larger than the longitudinal(streamwise)gradients for these flows,the original Navier Stokes equations are parabolized in the streamwise direction.A simple model,based on Boussinesq hypothesis,is used for turbu- lent flow.The discretized equations are then solved step by step in the streamwise direction,using an iterative procedure at each station.Numerical solutions have been obtained for different parameters,such as the Reynolds number,the circulation and the initial position of the vortices.The computed flow patterns and the skin friction coefficient and Stanton number are found to be qualitatively consistent with available experimental results.It is shown that the interaction between the vortices and the boundary layer may severely disturb the boundary layer flow field and thus considerably increase the local skin friction and heat transfer rate on surface of an aircraft.展开更多
文摘The interaction between longitudinal vortices and flat plate boundary layer has been studied numerically for both laminar and turbulent flow situations.The vortices are assumed to be placed in an otherwise two-dimensional boundary layer flow.The flow is assumed to be incompressible and steady.Consid- ering the fact that the velocity,vorticity and temperature gradients in the transverse directions are much larger than the longitudinal(streamwise)gradients for these flows,the original Navier Stokes equations are parabolized in the streamwise direction.A simple model,based on Boussinesq hypothesis,is used for turbu- lent flow.The discretized equations are then solved step by step in the streamwise direction,using an iterative procedure at each station.Numerical solutions have been obtained for different parameters,such as the Reynolds number,the circulation and the initial position of the vortices.The computed flow patterns and the skin friction coefficient and Stanton number are found to be qualitatively consistent with available experimental results.It is shown that the interaction between the vortices and the boundary layer may severely disturb the boundary layer flow field and thus considerably increase the local skin friction and heat transfer rate on surface of an aircraft.
