Thin　liquid　film　evaporation　is　a　prevailing　cooling　technique　for　thermal　protection　to　the　inner　wall　of　a　chamber　with　high-intensity　combustion.　A　novel　model　is　developed　to　investigate　the　flow　and　evaporation　of　liquid　film　in　a　rocket　combustion　chamber　with　high　temperature　and　high　shear　force,　in　which　shear　stress　at　the　interface　between　liquid　film　and　high　temperature　combustion　gas　with　high　velocity,　capillary　pressure　of　liquid　and　disjoining　pressure　associated　with　liquid　film　evaporation　are　taken　into　account.　A　numerical　algorithm　of　the　backward　solution　is　deliberately　adopted　to　solve　this　model　so　as　to　eliminate　the　entrance　effect　caused　by　different　inlet　conditions　of　liquid　film.　For　given　temperature　and　hot　gas　rate　in　a　chamber,　a　stably　evolution　regime　of　liquid　film　with　the　thickness　from　thick　to　thin　is　depicted　corresponding　to　the　total　process　of　being　sheared　into　film　and　being　evaporated　to　dryness.　Results　indicate　that　the　three　forces　mentioned　above　play　critical　parts　in　flowing　and　evaporating　of　liquid　film　during　its　different　evolution　regimes.　It　was　shown　that　shear　stress　and　capillary　pressure　have　a　positive　effect　on　the　flow　and　evaporation　of　film,　as　well　as　a　negative　effect　from　the　disjoining　pressure.　The　effects　of　these　forces　are　different　dependent　on　different　initial　average　thickness　of　film,　and　the　distribution　profile　of　these　forces　are　totally　illustrated　in　detailed.　The　prediction　of　liquid　film　length,　from　being　injected　to　being　evaporated,　by　the　proposed　model　is　in　a　good　agreement　with　available　experimental　data.　All　findings　are　expected　to　provide　a　fundamental　guideline　for　the　design　and　optimization　of　efficient　thermal　protect　to　the　combustion　chamber　of　space　engine.　©　2021　Elsevier　Masson　SAS