The internal flow-field of a dual combustor scramjet, without fuelinjection and combustion, was studied in this paper. The experiment wascarried out in a shock tunnel, and schlieren photographs of the flow ininlet and dual-combustor were obtained for the first time. TVD schemewas used to solve the three-dimensional, complete Navier-Stokesequations by zoned numerical simulations for the nozzle and scramjet. Inthe meantime, several geometrical parameters were varied to show theireffects on the flow field. For a typical case, i. e. hp=12.93 mm,the computed waves are similar to that in the photograph, and staticpressures along the lower wall are also in agreement with experimentalones. The flow in the inlet, supersonic combustor and aft nozzle isrelatively simple, but rather complex in the subsonic combustor. Alongthe lower wall, the separated flow evolves into a contact surface tillsubsonic combustor entrance. By reducing hp, shifting splitter upwardsand rotating splitter clockwise, the recirculation zone moves upstreamalong the wall to the inlet, and contact surface is raised up when theinflow parametors remain unchanged. In mostcases, contact surfaces along the lower wall are seriously distorted.Overflow will occur at the entrance of subsonic combustor. Then, theflow will be choked in the duct.
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