Numerical analysis of air flow past an unmanned aerial vehicle with internal propulsion system

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F17%3A00329194" target="_blank" >RIV/68407700:21220/17:00329194 - isvavai.cz</a>

Výsledek na webu

<a href="http://dx.doi.org/10.3233/JCM-160673" target="_blank" >http://dx.doi.org/10.3233/JCM-160673</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.3233/JCM-160673" target="_blank" >10.3233/JCM-160673</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Numerical analysis of air flow past an unmanned aerial vehicle with internal propulsion system

Popis výsledku v původním jazyce

According to the evolution of unmanned aerial vehicles (UAV), several investments have been increasing every year, especially in the field of aerodynamic characteristics. This paper deals with the prediction of pressure and velocity fields on a UAV with internal propulsion system using computational fluid dynamics. The main objective is to evaluate the effect of the air flow past the aircraft and how this affects the aerodynamic performance by means of obtaining lift and drag forces. The airfoil of this aircraft is the 2415-3S, which was developed in previous research [ 1]. Since the computational domain is three-dimensional and complex, a hybrid mesh was developed and validated with a convergence study. Both the computational domain and the numerical solution were developed with commercial CAD and CFD software respectively. Air, incompressible and steady was simulated with a Reynolds number of 2.74 x 10(5). The selected turbulence model was Spalart-Allmaras which has been designed specifically for aerospace applications involving wall-bounded flows. Lift, drag and moment coefficients as well as pressure and velocity contours were obtained at different angles of attack. Experimental results will be obtained in future work to be compared to numerical ones and achieve the validation.

Název v anglickém jazyce

Numerical analysis of air flow past an unmanned aerial vehicle with internal propulsion system

Popis výsledku anglicky

According to the evolution of unmanned aerial vehicles (UAV), several investments have been increasing every year, especially in the field of aerodynamic characteristics. This paper deals with the prediction of pressure and velocity fields on a UAV with internal propulsion system using computational fluid dynamics. The main objective is to evaluate the effect of the air flow past the aircraft and how this affects the aerodynamic performance by means of obtaining lift and drag forces. The airfoil of this aircraft is the 2415-3S, which was developed in previous research [ 1]. Since the computational domain is three-dimensional and complex, a hybrid mesh was developed and validated with a convergence study. Both the computational domain and the numerical solution were developed with commercial CAD and CFD software respectively. Air, incompressible and steady was simulated with a Reynolds number of 2.74 x 10(5). The selected turbulence model was Spalart-Allmaras which has been designed specifically for aerospace applications involving wall-bounded flows. Lift, drag and moment coefficients as well as pressure and velocity contours were obtained at different angles of attack. Experimental results will be obtained in future work to be compared to numerical ones and achieve the validation.

Druh

J_SC - Článek v periodiku v databázi SCOPUS

CEP obor

—

OECD FORD obor

20302 - Applied mechanics

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2017

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

Journal of Computational Methods in Sciences and Engineering

ISSN

1472-7978

e-ISSN

1875-8983

Svazek periodika

17

Číslo periodika v rámci svazku

1

Stát vydavatele periodika

NL - Nizozemsko

Počet stran výsledku

10

Strana od-do

199-208

Kód UT WoS článku

000397898800019

EID výsledku v databázi Scopus

2-s2.0-85019673195