The　coaxial　Tri-rotor　micro　air　vehicle　(MAV)　is　composed　of　three　coaxial　rotors　where　the　aerodynamic　characteristics　of　is　complicated　in　flight　especially　when　the　wind　effect　is　introduced.　In　this　paper,　the　hovering　performance　of　a　full-scale　coaxial　Tri-rotor　MAV　is　analyzed　with　both　the　simulations　and　wind　tunnel　experiments.　Firstly,　the　wind　effect　on　the　aerodynamic　performance　of　coaxial　Tri-rotor　MAV　is　established　with　different　rotor　speed　(1500-2300　rpm)　and　horizontal　wind　(0-4　m/s).　Secondly,　the　thrust　and　power　consumption　of　coaxial　Tri-rotor　(L/D　=　1.6)　were　obtained　with　low-speed　wind　tunnel　experiments.　Furthermore,　the　streamline　distribution,　pressure　distribution,　velocity　contour　and　vortex　distribution　with　different　horizontal　wind　conditions　are　obtained　by　numerical　simulations.　Finally,　combining　the　experiment　results　and　simulation　results,　it　is　noted　that　the　horizontal　wind　may　accelerate　the　aerodynamic　coupling,　which　resulting　in　the　greater　thrust　variation　up　to　9%　of　the　coaxial　Tri-rotor　MAV　at　a　lower　rotor　speed.　Moreover,　the　aerodynamic　performance　is　decreased　with　more　power　consumption　at　higher　rotor　speed　where　the　wind　and　the　downwash　flow　are　interacted　with　each　other.　Compared　with　no　wind　flow,　the　shape　of　the　downwash　flow　and　the　deformation　of　the　vortex　affect　the　power　loading　and　figure　of　metric　accordingly.