CFD Simulation of a Wing-In-Ground-Effect UAV

[摘要] This paper reports a numerical analysis on a wing section used for a Wing-In-Ground-Effect (WIG) unmanned aerial vehicle (UAV). The wing geometry was created by SolidWorks and the incompressible Reynolds-averaged Navier-Stokes (RANS) equations were solved with the Spalart-Allmaras turbulence model using CFD software ANSYS FLUENT. In FLUENT, the Spalart-Allmaras model has been implemented to use wall functions when the mesh resolution is not sufficiently fine. This might make it the best choice for relatively crude simulations on coarse meshes where accurate turbulent flow computations are not critical. The results show that the lift coefficient and lift-drag ratio derived excellent performance enhancement by ground effect. However, the moment coefficient shows inconsistency when the wing is operating in very low altitude - this is owing to the difficulty on the stability control of WIG vehicle. A drag polar estimation based on the analysis also indicated that the Oswald (or span) efficiency of the wing was improved by ground effect.

[发布机构] Interdisciplinary Division of Aeronautical and Aviation Engineering, Hong Kong Polytechnic University, Hong Kong, Hong Kong^1;Department of Mechanical Engineering, Hong Kong Polytechnic University, Hong Kong, Hong Kong^2

[效力级别] 机械制造 [学科分类] 航空航天科学

[关键词] Moment coefficient;Performance enhancements;Reynolds averaged Navier Stokes (RANS)equations;Spalart-Allmaras model;Spalart-Allmaras turbulence model;Stability control;Turbulent flow computation;Wing in ground effect