Topic of this bachelor thesis is the performance analysis of a fully electric, acrobatic aircraft in horizontal flight and climbing, as well as the comparison of the same with the equivalent aircraft powered by a piston engine. Beside estimation of the drag, features of the propulsion system required for this analysis are also modelled. Analysed aircraft and its characteristics are based upon currently very attractive and interesting, fully electric aircraft-Extra 330LE, which is compared to the model of equally capable aircraft Extra 330LX. After collecting available performance data, achievements, and features of both planes, initial geometry is adopted and drag coefficient is estimated. Then, the features of the propulsion system are determined as well as performance results which are then compared not just between two differently powered planes, but also to the initial performance and achievements of the actual Extra 330LE and Extra 330LX aircraft. Aircraft performance is calculated using the total energy method, for a plane in a horizontal flight, and with use of the equations of motion for the center of gravity of an aircraft in climbing regime. The analysis results include the flight envelope of the aircraft with all relevant limits as well as minimum time to climb performance.