Secondary separation phenomena in three-dimensional shock wave/turbulent boundary layer interaction regions induced by sharp fin and blunt fin have been investigated. A color oil source method, in which various color oil are oozed through many holes on the interaction surface, are applied for details visualization of separated region as well as conventional oil flow technique.
For sharp fin separated region increases as attach angle is increased. Also at higher attack angle a separated region is divided into two parts. The outer part is located next to the primary separation line and oil flow lines are almost parallel to the primary separation line. The inner part is located between the outer part and fin and 'S' type oil flow lines are quite significant.
For blunt fin separated region at freestream Mach number of 2, 3 and 4 are visualized. The results show separated flow patterns changes between Mach number 3, and 4. Also at Mach number of 4, secondary separation region become quite obvious by using the color oil source method.
