In　the　course　of　studying　the　principle　of　missile　flight,　the　conclusion　of　the　course　＇the　most　favorable　position　of　the　maximum　thickness　of　supersonic　airfoil　is　behind　the　midpoint　of　the　airfoil＇[1]　makes　me　very　puzzled.　By　looking　up　information,　the　serial　design　of　supersonic　airfoil　is　difficult　and　the　period　is　long　at　present.　This　paper　takes　the　maximum　thickness　position　as　the　variable　and　optimizes　through　multidisciplinary　design　(Multidisciplinary　Design　Optimization,　MDO)　[2].　The　software　Isight,　integrates　the　self-compiled　C　language　program　and　CFD　software,　designs　a　set　of　automatic　operation　optimization　flow,　and　finally　obtains　the　optimal　solution　of　lift-to-drag　ratio　under　different　maximum　thickness　through　iterative　calculation,　and　then　verifies　the　influence　of　maximum　thickness　position　on　missile　aerodynamic　force,　and　optimizes　the　design　flow　to　shorten　the　design　period.　©　2020　ACM.