Aircraft energy maneuverability and modeling of performance parameters with metaheuristic methods

Within the scope of this thesis; a method is presented to obtain specific excess power (Ps) contours, which show the performance limits of the aircraft, present the altitude and speed combinations at which they can fly at different specific excess powers, and help determine the trajectory corresponding to the minimum time to climb without the need for any mathematical operation. The method presented for the B737-800 aircraft includes the aircraft performance model, which consists of aerodynamic, thrust and fuel flow rate models, and the Ps model. The actual climb thrust data of the PW4056 turbofan engine is used for the thrust model. In the model created for this engine, it is taken into account that the thrust is a function of altitude, so it changes with temperature, density, pressure and is also a function of Mach number. Real flight data record (FDR) data of the B737-800 aircraft were used in all models except the thrust model. The fuel flow rate model allows the calculation of the weight force, which is important for obtaining Ps contours with high accuracy, and which is constantly decreasing due to fuel consumption during the flight. In the aerodynamic model, the increase in compressible drag at Mach values above the critical Mach number and profile camber are considered. Ps contours were obtained using the aircraft performance model. The curve data is the source data for the Ps model created afterward. This study presents a method on how to obtain the climb trajectory estimation and Ps contours of an aircraft if real FDR data is available. The cuckoo search algorithm (CSA) method was used to create the models. Particle swarm optimization (PSO) method, which is a different metaheuristic method, was used to validate the CSA models. Accurate results were obtained with both metaheuristic methods in all of the optimization processes performed using the Matlab program.