Hybrid rockets are a type of chemical rocket propulsion where the reactants are in different phases. Historically, hybrid rockets have been underutilized in the aerospace industry. However, due to their simple nature, they are easy to construct and test. Research on hybrid rocket propulsion was conducted using optically clear polymethylmethacrylate and gaseous oxygen with a nozzle designed to achieve Mach 2. Characterization was performed using combustion simulations available from NASA and measurements with pressure transducers, thermocouples, a load cell, and high-speed cameras. The test stand and hybrid rocket itself were designed by previous senior design groups. From the results, performance parameters such as the characteristic velocity, thrust coefficient, and specific impulse were calculated for various test times and oxidizer mass flow rates. Testing has shown that the rocket can be run safely and successfully numerous times.