Shockwaves can sharply increase the temperature and pressure of a gas in a reliable and near-instantaneous manner, leading to their utility of producing desirable conditions for the study of chemical combustion and high-speed gas dynamics. Shock tubes effectively produce regions of high-pressure, high-temperature gas by generating shockwaves that reflect off of the end of the driven section and form a reflected shockwave. Though the flow conditions after this sequence are typically assumed to be steady, phenomena such as the growth and interaction of the boundary layer with the reflected shockwave cause non-ideal fluctuations in these parameters. The effect of the Reynolds number of the flow behind the incident shockwave on these flow phenomena was studied using a newly built test section added to the shock tube facility of the High-Speed Aerothermodynamics Laboratory at the University of Oklahoma. High-speed schlieren imaging and pointwise pressure measurements were used to assess the reflected normal shockwave/boundary layer interaction (SBLI) and pressure fluctuations present in the flow. It was found that increasing the freestream Reynolds number helped decrease the size of the shockwave bifurcation formed from the SBLI while also reducing the amount of pressure fluctuations in the region behind the reflected shockwave. These trends persisted across experiments performed at three distinct shock Mach numbers.