Aerodynamic　characteristics　of　small-rotor　were　studied　based　on　the　finite　volume　method.　In　an　attempt　to　study　its　performance,　hovering　flow　field　of　the　single-rotor　was　established,　meanwhile,　the　boundary　conditions　were　set　up.　In　addition,　flow　field　was　analyzed　numerically　by　using　computational　fluid　dynamics　method　(CFD)　which　aimed　at　obtaining　the　distribution　of　surface　pressure,　the　diagram　of　velocity　vector　and　the　flow　chart　of　flow　field.　Simultaneously,　the　coefficients　of　lift　and　drag　were　acquired　by　data　processing.　In　the　analysis　of　the　distribution　features　got　from　the　numerical　simulation　of　flow　field,　aerodynamic　characteristics　of　the　rotor　were　revealed　generally.　Equally　important,　experimental　research　and　hover　test　stand　were　also　designed　to　measure　the　actual　thrust　and　power　consumption　of　the　system.　Compared　the　results　of　numerical　simulation　with　experimental　verification,　the　speed　range　of　higher　lift-to-drag　ratio　and　lower　power　consumption　of　a　single-rotor　were　obtained.