Analiza pretoka zraka okoli aeroprofila s panelno metodo

zaključna naloga Razvojno raziskovalnega programa I. stopnje Strojništvo

Adam Plantarič (Author), Viktor Šajn (Mentor), Miha Brojan (Co-mentor)

Abstract

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.

Keywords

diplomske naloge;Bernoullijeva enačba;potencialni tok;panelna metoda;Kuttov pogoj;Kutta - Žukovski teorem;aeroprofili;

Data

Language:	Slovenian
Year of publishing:	2020
Typology:	2.11 - Undergraduate Thesis
Organization:	UL FS - Faculty of Mechanical Engineering
Publisher:	[A. Plantarič]
UDC:	532.6:629.7(043.2)
COBISS:	22661635
Views:	900
Downloads:	243
Average score:	0 (0 votes)
Metadata:

Other data

Secondary language:	English
Secondary title:	Analisys of air flow around airfoil using panel method
Secondary 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.
Secondary keywords:	thesis;Bernoulliʹs equation;potential flow;panel method;Kutta Condition;Kutta - Joukowski theorem;airfoils;
Type (COBISS):	Final paper
Study programme:	0
Embargo end date (OpenAIRE):	1970-01-01
Thesis comment:	Univ. v Ljubljani, Fak. za strojništvo
Pages:	XI, 54 f.
ID:	11895239