To design a three-dimensional turbine based combined cycle (TBCC) exhaust system

a design approach was presented. It employed osculating method based on flowfield of nozzle with optimum thrust to design a three-dimensional section controllable dissymmetric ramjet nozzle. And on the basis of curved ramjet flowpath

a new scheme of rotating and sliding the shared surface was proposed to regulate the throat area of the turbojet nozzle. Cold flow experiments and numerical simulations were conducted at typical test points. The comparison proved that the design approach of TBCC exhaust system is practicable. Under the ramjet mode

the comparison of static pressure distributions showed agreement and the relative root mean square error was less than 10.8%. Under the other modes

obvious deviations appeared in the area where the shock wave interacted with the boundary layer

the maximum relative error was 30.6%. However

the variation tendencies of the static pressure distributions were consistent.