Based　on　the　three-dimensional　viscous　compressible　Navier-Stokes　equations,　the　aerodynamic　characteristics　of　supersonic　rocket　sled　flying　near　the　ground　were　analyzed.　The　k-ω　turbulence　model　were　used　in　the　numerical　simulation.　Triangular　grid　and　quadrilateral　grid　were　used　to　divide　the　computational　domain,　and　the　finite　volume　method　was　adopted　to　discretize　the　governing　differential　equations,　and　the　above　equations　were　solved　by　the　implicit　coupling　algorithm.　The　effects　of　velocity　and　attack　angle　on　the　aerodynamic　characteristics　were　numerically　simulated.　The　results　show　that　the　surface　pressure　of　the　rocket　head　increases　with　the　increase　of　Mach　number;　the　head　of　the　rocket　flying　at　supersonic　speed　generates　shock　waves;　the　drag　coefficient　first　gradually　increases　and　then　decreases　with　the　increase　of　Mach　number.　Under　the　conditions　of　small　attack　angle,　the　drag　and　the　lift　change　little,　but　the　lateral　force　increases　significantly　with　the　increase　of　yaw　angle.　The　results　offer　reference　for　the　design　of　the　supersonic　rocket　sled.