In this thesis, stall was modeled in Simulink for IR-1, aircraft similar to the Dassault Rafale. Based on already obtained data, coefficients nedeed for creating the model were chosen. The lift coefficients, drag coefficients and pitch moment coefficients among with lateral coefficients for roll and yaw, are implemented in the Simulink model for high angles of attack, from 10 to 60 degrees. After collecting the data and modifying the model, an experiment was conducted with a pilot in the loop. The existing IR-1 aircraft model, was analyzed on a flight simulator on a sample of ten subjects. For the purposes of the experiment, candidates were given two tasks of saving the aircraft from stall conditions. The first task consists of approaching the stall and immediately after the signal, i.e. the moment when the angle of attack reaches 25 degrees, getting out of the extreme situation. The following task is to approach to deep stall conditions, and right after the angle of attack has reached 30 degrees, retract the aircraft. Each of the candidates completed the NASA Task Load Indeks questionnaire and rated the manouverability of the model according to the Cooper-Harper scale for both tasks. After the experiments, a subjective and objective naalysis of the results as carried out. The analysis of the results includes the verification of the conclusions obtained from the trim flight analysis and the analysis of lateral aerodynamics from the calculations done before experiments.