Analiza pretoka zraka okoli aeroprofila s panelno metodo

Plantarič, Adam (author), Šajn, Viktor (mentor), Brojan, Miha (comentor)

Panelna metoda omogoča analizo pretoka fluida okoli aeroprofila, pri čemer je predpostavljen neviskozen in nestisljiv fluid. S panelno metodo je mogoče analizirati pretok fluida okoli aeroprofila poljubne oblike. Določimo lahko koeficient vzgona aeroprofila in se pri tem pri majhnih vpadnih kotih aeroprofila dobro približamo realnim vrednostim koeficienta vzgona (pridobljenim s CFD analizo ali z eksperimentalnim delom). V delu je podrobno opisana panelna metoda za modeliranje pretoka zraka okoli aeroprofila krila zrakoplova in predstavljen je izračun polare izbranega aeroprofila, pridobljene z uporabo panelne metode. Zatem z opisano panelno metodo izračunamo graf odvisnosti koeficienta vzgona od vpadnega kota izbranega profila in rezultate primerjamo z rezultati CFD (Computational Fluid Dynamics) analize in z eksperimentalno pridobljenimi vrednostmi. Ugotovimo, kakšna so odstopanja rezultatov panelne metode in kakšen je interval uporabe panelne metode.

• Language: Slovenian
• Keywords: Bernoullijeva enačba, potencialni tok, panelna metoda, Kuttov pogoj, Kutta - Žukovski teorem, aeroprofili
• Work type: Bachelor thesis/paper
• Typology: 2.11 - Undergraduate Thesis
• Organization: FS - Faculty of Mechanical Engineering
• Place of publishing: Ljubljana
• Publisher: [A. Plantarič]
• Year: 2020
• Number of pages: XI, 54 str.
• PID: 20.500.12556/RUL-117474
• UDC: 532.6:629.7(043.2)
• COBISS.SI-ID: 22661635
• Publication date in RUL: 11.07.2020

PLANTARIČ, Adam, 2020, Analiza pretoka zraka okoli aeroprofila s panelno metodo [online]. Bachelor’s thesis. Ljubljana : A. Plantarič. [Accessed 11 April 2025]. Retrieved from: https://repozitorij.uni-lj.si/IzpisGradiva.php?lang=eng&id=117474

Secondary language

• Language: English
• Title: Analisys of air flow around airfoil using panel method

Abstract

Panel method allows us to analyze fluid flow around airfoil, where nonviscous and incompressible fluid is assumed. Panel method can be used to analyze fluid flow around airfoil of any chosen shape. We can determine lift coefficient and doing so, we come close to real values (obtained with CFD analysis or experimentally) of lift coefficient at small angles of attack. In the thesis, panel method, used for modeling air flow around wing of aircraft, is described in detail and computation of lift coefficient as a function of angle of attack, obtained using panel method, is introduced. Afterward, we compute graph of lift coefficient as a function of angle of attack of chosen airfoil, and we compare the results with results of CFD (Computational Fluid Dynamics) and with experimentaly obtained values. We determine deviations of results of panel method and lastly we determine interval of panel method usage.

• Keywords: Bernoulli’s equation, potential flow, panel method, Kutta Condition, Kutta - Joukowski theorem, airfoils