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<p>Ground effect studies have been a talk of the subject in recent years due to their improved aerodynamic efficiency during take-off and landing approaches for an unmanned air vehicle designed with a high aspect ratio wing. Towards this, an attempt has been made to understand the ground effect by using a computational approach based on the articles published in an open domain. For this purpose, a high aspect ratio wing vehicle is designed using Wortmann FX 63-137 airfoil. A commercial CFD software Fluent, along with the <InlineEquation ID="IEq1"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="12046_2025_2838_Article_IEq1.gif" Format="GIF" Height="17" Rendition="HTML" Resolution="72" Type="Linedraw" Width="117" /> </InlineMediaObject> <EquationSource Format="TEX">\(SST-{\gamma }-Re_{\theta }\)</EquationSource> <EquationSource Format="MATHML"><math> <mrow> <mi>S</mi> <mi>S</mi> <mi>T</mi> <mo>-</mo> <mi>γ</mi> <mo>-</mo> <mi>R</mi> <msub> <mi>e</mi> <mi>θ</mi> </msub> </mrow> </math></EquationSource> </InlineEquation> transition model, is used to characterize the flow phenomena around the vehicle. A ground effect is simulated by using a moving wall boundary condition. It is observed that the ground effect significantly influences the longitudinal aerodynamic coefficients like lift, drag and pitching moment when the vehicle is in close proximity to the ground. The vortex deformation in the downstream direction of the fuselage becomes stronger in the ground effect than in the freestream. The volume streamlines over the wing surface at different heights are shown in ground effects and freestream. Further, aerodynamic coefficients over a vehicle with and without ground effects are compared.</p>

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Ground effect studies on unmanned air vehicle with high aspect ratio wing

  • 期刊论文

  • 发表日期：

    2025年7月24日

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  • Vishal S Shirbhate,
  • K Siva Kumar,
  • Kiran Chutkey,
  • Azhar Ali Mohammed,
  • Ajay Krishna

摘要

Ground effect studies have been a talk of the subject in recent years due to their improved aerodynamic efficiency during take-off and landing approaches for an unmanned air vehicle designed with a high aspect ratio wing. Towards this, an attempt has been made to understand the ground effect by using a computational approach based on the articles published in an open domain. For this purpose, a high aspect ratio wing vehicle is designed using Wortmann FX 63-137 airfoil. A commercial CFD software Fluent, along with the \(SST-{\gamma }-Re_{\theta }\) S S T - γ - R e θ transition model, is used to characterize the flow phenomena around the vehicle. A ground effect is simulated by using a moving wall boundary condition. It is observed that the ground effect significantly influences the longitudinal aerodynamic coefficients like lift, drag and pitching moment when the vehicle is in close proximity to the ground. The vortex deformation in the downstream direction of the fuselage becomes stronger in the ground effect than in the freestream. The volume streamlines over the wing surface at different heights are shown in ground effects and freestream. Further, aerodynamic coefficients over a vehicle with and without ground effects are compared.