The　nonlinear　vibration　of　a　two-dimensional　composite　laminated　plate　in　subsonic　air　flow　with　simply　supported　boundary　conditions　is　investigated.　Based　on　the　von　Karman＇s　plate　theory,　the　equation　of　motion　of　the　plate　is　established　using　Hamilton＇s　principle.　The　aerodynamic　pressure　induced　by　the　coupled　vibration　of　the　plate　and　subsonic　airflow　is　derived　from　the　linear　potential　flow　theory　and　compared　with　the　existing　model.　The　variable　separation　method　is　used　to　transform　the　equation　of　motion　of　the　plate　into　nonlinear　ordinary　differential　equations.　The　influences　of　the　flow　velocity,　the　length-to-thickness　ratio　and　the　ply　angle　of　the　plate　on　the　nonlinear　vibration　behaviors　of　the　plate　are　discussed.　From　the　analytical　and　numerical　results　it　can　be　seen　that　the　critical　instability　velocity　obtained　from　the　present　aerodynamic　model　is　the　same　as　the　existing　result.　The　first-order　expansion　of　the　transverse　displacement　can　reflect　the　dynamic　characteristics　of　the　plate.　With　the　increase　of　the　flow　velocity　and　the　length-to-thickness　ratio,　the　instability　interval　of　the　nonlinear　vibration　can　be　prolonged　and　the　nonlinear　resonance　frequency　can　be　increased.　The　composite　laminated　plate　with　smaller　ply　angle　exhibits　more　stable　dynamic　properties　than　that　with　larger　ply　angles.