In view of the problem that the higher inlet total temperature of tandem TBCC nozzle can reduce the ablation of the wall material

a film-cooling scheme adapted to different flight Mach numbers in the flight envelope was presented

showing a significant effect on the thermal protection of the nozzle. The cooling effect for different flight Mach numbers based on the CFD method was calculated. The research indicates that there will be a more noticeable change of the flow field conditions nearby the rhomboid slots than annular slots. After film-cooling

the temperature of nozzle has a 1000K's decline than before. The film-cooling adiabatic efficiency of the downstream wall centerline can reach to 0.9 at most flight Mach numbers. The downstream wall temperature of the slot is mainly distributed symmetrically along the span of the nozzle

and the temperature uniformity gradually declines with x's increment.