Supersonic　flutter　behaviors　of　functionally　graded　material　(FGM)　shallow　conical　panel　with　steady　thermal　stress　are　investigated.　It　is　assumed　that　temperature　dependent　material　properties　are　graded　along　the　radial　direction　following　power　law　form.　The　shallow　conical　panel　is　formulated　with　the　aid　of　first-order　shear　deformation　theory　and　von-Karman　geometrical　nonlinearity.　The　aerodynamic　loads　are　evaluated　by　using　the　first-order　piston　theory.　The　equations　of　motion　in　the　form　of　nonlinear　partial　differential　are　derived　by　applying　the　Hamilton＇s　principle.　In　order　to　get　a　high　dimensional　dynamic　discrete　system,　the　Galerkin＇s　method　is　utilized　and　this　system　includes　the　effect　of　steady　thermal　stress　due　to　considering　the　thermal　stress.　Newton-Raphson　method　and　continuation　method　are　applied　to　obtain　the　equilibrium　points,　and　flutter　boundaries　are　analyzed　by　solving　the　eigenvalue　problem.　The　influences　of　damping,　ratio　of　length　to　thickness　and　volume　fraction　index　on　the　flutter　characteristics　of　the　simply　supported　FGM　shallow　conical　shell　panel　are　studied.