Change of Stability Parameters as a Result of Different Swept Angle Variations for a Fixed Wing Unmanned Aerial Vehicle

<p class="MsoNormal" style="margin-top:0cm;margin-right:0cm;margin-bottom:6.0pt;margin-left:18.0pt;text-align:justify"><span lang="EN-GB" style="font-size:12.0pt;line-height:115%;font-family:&quot;Times New Roman&quot;,&quot;serif&quot;">In this study effect ofone of the wing geometric specialty called as swept angle,<i> “Λ”</i>, onlongitudinal and lateral stability is examined computationally. At fixedthrottle longitudinal and lateral stability parameters examined for doubleswept angle having wing. In order to examine effect of swept on stability wingis built with two swept angles. The first swept angles starts in theintersection position of wing and body. In this position the used swept anglesare <i>Λ₁</i>= [5°,10°,15°]&nbsp;and for the second position where it is mid position of the wing&nbsp; the used swept angles are <i>Λ₂</i>=[15°,20°,25°]. By using XFLR5 analysis program 9 different combination of withtwo different swept angle positions are analyzed as a result of these analysesresulting stability parameters are obtained. By using these parameters dampingratio “ζ” and undamped natural frequency “ω_n” are compared. Thiswork has been supported by Erciyes University Scientific Research ProjectsCoordination Unity under grant number FBA-2024-14147.<o:p></o:p></span>