Calculation of Performance Data for Diamond DV20 Katana Aircraft

Pod pojmom performanse nekog zrakoplova podrazumijeva se sposobnost zrakoplova da pri određenim uvjetima leta (visina, brzina, masa) posjeduje što povoljnije karakteristike u vidu doleta, istrajnosti, što manje potrošnje goriva, optimalne duljine potrebne za polijetanje i slijetanje, itd. Pri samom početku ovog rada predstavljene su deklarirane performanse zrakoplova Diamond Katana DV20 koje se nalaze u njegovom operativnom priručniku. U nastavku rada opisan je model propulzije zrakoplova koji se koristi u sljedećim poglavljima skupa sa aerodinamičkim modelom iz rada Petra Papočija za izračun performansi zrakoplova u fazi krstarenja i penjanja. Na temelju teorijskih izračuna dobivene su vrijednosti za maksimalnu istrajnost leta od 4,9 h, maksimalnu brzinu krstarenja od 236 km/h, maksimalnu brzinu uzdizanja od 4,8 m/s, te brzina za maksimalnu brzinu uzdizanja od 100 km/h. Na kraju ovog rada uspoređeni su podatci dobiveni u ovom radu s objavljenim podatcima o performansama. Temeljem usporedbe teorijski dobivenih podataka i deklariranih podataka može se zaključiti da da su odstupanja minimalna i prihvatljiva.The term performance of an aircraft means the ability of an aircraft to to have the mosta efficient characteristics under certain conditions (altitude, speed, mass) in form of flight endurance, range, fuel consumption, length required for take off and landing, etc. At the beginning of this paper are presented performance of the aircraft Diamond Katana DV20 which are found in it′s manual. The following section of the paper describe the model of propulsion, used in aircraft, along with aerodynamic model form the work of Petar Papoči, to calculate performance of this aircraft in the cruise and climb phase. At the end of this paper, the data obtained in this paper will be compared with the published performance data. In accordance with theoretical calculation the given figure for maximum flight endurance is 4,9 h, maximum cruising Zagreb, 2019. speed is 236km/h, maximum lifting speed is 4,8 m/s, and the speed for maximum velocity is 100km/h. At the end of this paper the data acquired during theoretical research was compared to the published performance data of the aircraft. Based on the comparison between the theoretically obtained data and the declared performance data it can be concluded that deviations in data are minimal and acceptable