Optimizacija oblika krila male bespilotne letjelice primjenom proširene metode noseće linije za proračun uzgona i otpora

undergraduate thesis

• Title (english): Small unmanned aerial vehicle wing shape optimization using extended lifting line method for lift and drag calculation
• Author: Petar Grabar
• Mentor: Pero Prebeg (mentor)
• Granter: University of Zagreb; Faculty of Mechanical Engineering and Naval Architecture; Zagreb
• Defense date and country: 2024-02-29, 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: optimizacija; uzgon; otpor; Weissinger; П vrtlog; panel; CPACS
• Keywords (english): optimization; lift; drag; Weissinger; П vortices; panel; CPACS
• Language: croatian
• URN:NBN: urn:nbn:hr:235:782770
• Study programme: Title: 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 resource: Text
• File origin: Born digital
• Access conditions: Open access
• Created on: 2024-02-22 12:05:14