Aircraft trim and performance analysis based on aerodynamic model identified from flight test

Zadatak završnog rada je provjera utjecaja modela aerodinamičkih koeficijenata na performanse zrakoplova u režimu ravnotežnog, horizontalnog leta. Prikazani su korišteni podaci za potrebe proračuna koji uključuju podatke o masi i raspodjeli mase, podatke o pogonskoj grupi zrakoplova i geometrijske karakteristike zrakoplova. Provedena je analiza ravnotežnog leta i u sklopu iste određene su polare zrakoplova. Za potrebe analize performansi, prikazane su i značajke pogonske grupe, temeljem Simulink modela motora, odnosno razvijene MATLAB funkcije za raspoloživu snagu. Iste funkcije, te ranije navedene jednadžbe polara, koriste se u daljnjoj analizi odabranih performansi. Od performansi promatra se ovojnica zrakoplova koja je određena za različite konfiguracije, odnosno za različite modele aerodinamičkih i pogonskih karakteristika te dolet i najdulje trajanje leta. Iz analize ravnotežnog leta važno je izdvojiti parametar napadnog kuta. U ovisnosti o napadnom kutu prikazane su aerodinamička finesa zrakoplova za maksimalni dolet i odnos uzgona i otpora za maksimalno trajanje leta. Analiziraju se performanse za zrakoplov generalne avijacije Piper PA-28 Warior III, a rezultati se uspoređuju s postojećima za ''mali putnički zrakoplov'' koji je nalik na Piper PA-28 180 Cherokee. Programski kodovi su pisani u MATLAB-u uz dodatno korištenje Simulink modela motora promatranog zrakoplova.The task of this bachelor thesis is to check the influence of aerodynamic coefficient models on aircraft performance in equilibrium horizontal flight. Data used for calculation purposes are presented, which include data on mass and mass distribution, data on aircraft propulsion group and geometric characteristics of aircraft. An equilibrium flight analysis was performed and the polar curves of the aircraft were determined. For the purposes of performance analysis, the characteristics of the powertrain based on the Simulink engine model or the developed MATLAB function for available power, are also presented. The same functions and the previously mentioned polar equations are used in further analysis of selected performances. From the performance, aircraft envelope is observed, which is determined for different configurations, ie. for different models of aerodynamic and propulsion characteristics, as well as the range and the longest flight duration. From the analysis of equilibrium flight, it is important to single out the parameter of the angle of attack. Depending on the angle of attack, the aerodynamic finesse of the aircraft for maximum range and the lift and drag ratio for maximum flight duration are shown. Performance for the Piper PA-28 Warior III general aviation aircraft is analyzed and the results are compared with those for the ''small comercial aircraft'' that is similar to the Piper PA-28 180 Cherokee. The program codes were written in MATLAB with the additional use of the Simulink model of the observed aircraft engine