Small gas turbine engines present a significantlylower performance when compared to large ones. The major reasons for that are the lower component efficiencies and size effects. The present work accomplishes an investigation of data available in the open literature for small turbojet and turbofan engines, covering a range from 1 to 5 kN of thrust, to find the most important parameters for these engine configurations. This study aims to evaluate the parameters used in engines in this thrust range, for the possible development of an engine for a specific application. This overview relies on a correlation between some of the major parameters of the engine, namely thrust, specific fuel consumption, pressure ratio, turbine inlet temperature, weight, length, diameter, and mass flow.