Proračun aerodinamičkih koeficijenata replike Penkalinog zrakoplova

Kovačevič, Ivan (2017) Proračun aerodinamičkih koeficijenata replike Penkalinog zrakoplova. = Penkala Airplane Replica Aerodynamic Coefficients Calculation. Undergraduate thesis , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Matijašević, Dubravko.

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Abstract (Croatian)

Replika Penkalinog zrakoplova konstruirana je za stogodišnjicu zrakoplovstva u Hrvat- skoj 2010. godine. Uspješno je obavila svoj prvi let, a nakon toga je svega nekoliko puta letjela. Naime, zapaženi su problemi u letu koji bi se trebali otkloniti kako bi let bio stabilan i siguran. U procesu usavršavanja tog zrakoplova potrebno je odrediti aerodinamičke koeficijente koji nikad nisu računati za cjelokupni zrakoplov što ćce biti napravljeno u ovome radu. Proračunat će se aerodinamički koeficijenti uzgona CL, induciranog otpora CDi jer se promatra bezvrtložno nestlačivo strujanje neviskoznog fluida te koeficijent momenta propinjanja Cm. Za analizu zrakoplova korišten je programski paket XFLR5 koji je osmišljen za analizu aeroprofila, krila i zrakoplova na malim Reynoldsovim brojevima. Zbog nedovoljnog poznavanja mogućnosti i točnosti navedenog paketa, dobiveni rezultati za aeroprofil i krilo bit će uspoređeni s rezultatima dobivenim jednakim metodama u programskom paketu MATLAB upotrebom znanja stečenih na kolegiju Aerodinamika 1 na studiju Zrakoplovstva Fakulteta Strojarstva i brodogradnje, Sveučilišta u Zagrebu. Metoda korištena za analizu aeroprofila je tzv. panelna metoda, dok su metode korištene za proračun ostatka zrakoplova: Prandtlova metoda noseće linije, Vortex Lattice Me- toda i 3D panelna metoda. Analiza je provedena tako da se vidi utjecaj pojedine komponente zrakoplova na pro- matrane aerodinamičke koeficijente. Razmatrat će se aeroprofil, krilo, krilo i trup te naposlijetku cjelokupna konfiguracija zrakoplova koja se sastoji od krila, trupa i repa. Aerodinamički koeficijenti prikazani su dijagramski uz polinome koji opisuju krivulje na dijagramima.

Abstract

A replica of Penkala's airplane was designed for the centenary of Croatian aviation in 2010. Its maiden flight was successful, but it has flown few times since. Several problems were detected during the flight, which must be removed for stable and safe future flying. For further airplane development it is necessary to calculate aerodynamic coefficients which have never before been calculated for the entire airplane. That is precisely what will be done in this thesis. Within steady uniform flow of incompressible fluid the airplane will be observed and lift CL, induced drag CDi and pitching Cm coefficients will be calculated. XFLR5 software will be used for the analysis. It is a tool for analysing airfoils, wings and planes operating at low Reynolds numbers. The lack of knowledge of this software was taken into consideration, and for this reason the results for the airfoil and wing will be compared with the results calculated by MATLAB software with codes learnt at Aerodynamic 1 course at the Faculty of Mechanical Engineering and Naval Architecture at the University of Zagreb. The method used for the airfoil analysis is the panel method, while the methods used for the analysis of the rest of the airplane are: Lifting Line Theory, Vortex Lattice Method and 3D Panel method. The analysis was conducted in a way to detect the influence of each component of the airplane on aerodynamic coefficients. The observed components are the airfoil, wing, wing and body, and at last the entire configuration of the airplane, composed of the wing, body and tail. Aerodynamic coefficients are shown in diagrams and supported by polynomials that describe curves on diagrams.

Item Type: Thesis (Undergraduate thesis)
Uncontrolled Keywords: replika; Penkala; XFLR5; aerodinamički; koeficijenti
Keywords (Croatian): replica; Penkala; XFLR5; aerodynamic, coefficients
Subjects: TECHNICAL SCIENCE
TECHNICAL SCIENCE > Aviation, rocket and space technology
TECHNICAL SCIENCE > Aviation, rocket and space technology > construction and establishment of a spacecraft
Divisions: 1300 Department of Aeronautical Engineering > 1320 Chair of Aircraft Dynamics
Date Deposited: 23 Feb 2017 10:49
Last Modified: 13 Mar 2017 13:45
URI: http://repozitorij.fsb.hr/id/eprint/7344

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