Hybrid rocket propulsion can be a viable solution for safe, high performance thrusters; as demanded by present day micro/nano satellite launchers. Among various hybrid propellant combinations, LO₂/HTPB+20%Al hybrid propellant combination offer a safe, high performance, low cost and scalable solution. In this study, lab level tests carried out with LO₂/HTPB+20%Al hybrid propellant combination is reported. The tests were conducted to study and improve the ignition and combustion characteristics of the motor. The ballistic performance of the hybrid motor is analyzed in depth. Potential improvements in test methodology and directions of future research are discussed.