Estimation of the fighter aircraft range

Tema ovog završnog rada jest analiza doleta i ostalih performansi borbenog zrakoplova korištenjem modela ravnotežnog leta, uz primjenu uvjeta za horizontalni let kao i usporedba istih s referentnim vrijednostima odabranog zrakoplova iščitanih iz tehničkog priručnika. Prije same numeričke analize, dolet, te sve karakteristike i metode vezane za računanje istog, detaljno su opisane. Procjeni doleta prethodi računanje ostalih značajki zrakoplova potrebnih za samu analizu. Te značajke dobivene su pokretanjem numeričkog modela za ravnotežni let u ovisnosti o različitim visinama, brzinama, konfiguracijama zrakoplova, te u ovisnosti o promjeni mase zrakoplova tijekom leta. Dobivene značajke ubacili smo u poseban program koji računa dolet za različite visine leta i različite konfiguracije zrakoplova. Osim iznosa doleta za svaku kombinaciju različite visine i konfiguracije, dobili smo iznose trajanja leta i mase rezervnog goriva za alternativna slijetanja. Usporedbom dobivenih rezultata, uočeno je prihvatljivo odstupanje od referentnih vrijednosti.Topic of this bachelor thesis is the analysis of range and other performance of a combat aircraft using model for trimmed aircraft, applying the horizontal flight conditions as well as comparing them with reference values of the selected aircraft, taken from the technical manual. Before the numerical analysis, the range, and all the characteristics and methods related to its calculation, are described in detail. The range assessment is preceded by the calculation of the other aircraft characteristics required for the analysis itself. These features were obtained by running a numerical model for trimmed flight as a function of different altitudes, velocities, aircraft configurations, and as a function of change in mass of the aircraft during the flight. We included the obtained features in a special program that calculates the range for different flight altitudes and different aircraft configurations. In addition to the resultes of range for each combination of different altitudes and configurations, we obtained the results of endurance and reserve fuel masses for alternative landings. By comparing the obtained results, acceptable deviation was observed