Abstract
An experimental method is presented for varying the effective aspect ratio (AReff) of a rectangular cross-section in a supersonic wind tunnel. An oblique shock wave is generated in a Mach 2 flow at flow deflection angles of 10° and 12°. The resulting shock wave boundary layer interactions (SWBLIs) at the tunnel wall are observed. A traversable shock generator allows the AReff of the wind tunnel to be varied and the relationship between the SWBLI and wind tunnel aspect ratio is studied for 1 < AReff < 1.5. Schlieren photography, surface oil flow visualization and Particle Image Velocimetry are used to investigate the flow. It is found that an increase in wind tunnel AReff is accompanied by the growth of the shockinduced boundary layer separation region. A Mach reflection was observed to form at AReff above 1.20 for the 12° SWBLI case. The stream-wise flow separation region on the floor is observed to grow proportionally to AReff .
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