Abstract
In order to create the transition criteria, or to control 3-D boundary layer flow, it is essential to know the detailed transition mechanism in advance. The main purpose of the present investigation is to make it clear the turbulent transition process in a swept cylinder boundary layer, which gives important fundamental information not only in the field of airbus drag reduction, but also in the field of space plane aerodynamic heat control.
Liquid crystal film is utilized to measure the transition region and streamwise streaks which corresponds to the crossflow vortics are visualized in color variation. These visualized color streaks enable us to find out the relation between velocity field and heat transfer rate which gives important fundamental information for aerodynamic heat effect on a swept wing or a delta wing surface. Detailed 3-D velocity measurement has been also performed using three-dimensional traversing equipment and rotatable hot wire.
