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undergraduate thesis
Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora
Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2024. urn:nbn:hr:235:782770
Grabar, Petar
University of Zagreb
Faculty of Mechanical Engineering and Naval Architecture

Institutional repository: Repository of Faculty of Mechanical Engineering and Naval Architecture University of Zagreb

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Grabar, P. (2024). Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora (Undergraduate thesis). Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture. Retrieved from https://urn.nsk.hr/urn:nbn:hr:235:782770

Grabar, Petar. "Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora." Undergraduate thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2024. https://urn.nsk.hr/urn:nbn:hr:235:782770

Grabar, Petar. "Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora." Undergraduate thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2024. https://urn.nsk.hr/urn:nbn:hr:235:782770

Grabar, P. (2024). 'Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora', Undergraduate thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, accessed 14 July 2024, https://urn.nsk.hr/urn:nbn:hr:235:782770

Grabar P. Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora [Undergraduate thesis]. Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture; 2024 [cited 2024 July 14] Available at: https://urn.nsk.hr/urn:nbn:hr:235:782770

P. Grabar, "Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora", Undergraduate thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Zagreb, 2024. Available at: https://urn.nsk.hr/urn:nbn:hr:235:782770

Metadata
TitleOptimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora
Title (english)Small unmanned aerial vehicle wing shape optimization using extended lifting line method for lift and drag calculation
AuthorPetar Grabar
MentorPero Prebeg (mentor)
GranterUniversity of Zagreb
Faculty of Mechanical Engineering and Naval Architecture
Zagreb
Defense date and country2024-02-29, Croatia
Scientific / art field,
discipline and subdiscipline		TECHNICAL SCIENCES
Aviation, Rocket and Space Technology
Aircraft Construction and Design
Abstract
U ovome radu, u programskom jeziku Python, izrađen je matematički model za optimizaciju krila male bespilotne letjelice. Distribucije sila otpora i uzgona računaju se pomoću proširene Prandtlove metode odnosno tzv. Weissingerovog modela koji opstrujavanje krila modelira П vrtlozima po rasponu krila. U radu je dan detaljan opis generiranja ulaznih podataka za Weissingerov model iz geometrije krila koji se može sastojati iz više trapeznih segmenata, sukladno CPACS zapisu modela krila. Također je korištena panelna metoda koja omogućuje izračunavanje koeficijenta uzgona aeroprofila u ovisnosti o napadnom kutu, a koja je korištena za korekciju rezultata Weissingerovog modela za nesimetrične aeroprofile. Izrađeni Python model primijenjen je na primjeru optimizacije male bespilotne letjelice.
Abstract (english)
In this thesis, a mathematical model for the optimization of the wing of a small unmanned aerial vehicle is developed using the Python programming language. The distributions of drag and lift forces are calculated using the extended Prandtl method, specifically the Weissinger model, which models wing airflow with П vortices along the wing span. The paper provides a detailed description of generating input data for the Weissinger model from the wing geometry, which can consist of multiple trapezoidal segments, in accordance with the CPACS data of the wing model. The panel method is also utilized, allowing for the calculation of the airfoil lift coefficient as a function of the angle of attack. This method is used to correct the results of the Weissinger model for non-symmetric airfoils. The developed Python model is applied to the optimization example of a small unmanned aerial vehicle.
Keywords
Keywords (english)
Languagecroatian
URN:NBNurn:nbn:hr:235:782770
Study programmeTitle: Aeronautical Studies
Study programme type: university
Study level: undergraduate
Academic / professional title: sveučilišni/a prvostupnik/ prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka zrakoplovnog inženjerstva (sveučilišni/a prvostupnik/ prvostupnica (baccalaureus/baccalaurea) inženjer/inženjerka zrakoplovnog inženjerstva)
Type of resourceText
File originBorn digital
Access conditionsOpen access
Terms of useLicence In copyright icon
Created on2024-02-22 12:05:14