Research On A Two-Dimensional Hypersonic Inlet Based On Dual-Mode Combustion

Investigation of a two-dimensional hypersonic inlet based on dual-mode combustion scramjetwas conducted by wind tunnel test and numerical simulation in this thesis, and also design methodresearch and study of its aerodynamic characteristics were carried out. The duct is divided into asupersonic duct and a subsonic combustion duct by a splitter plate. The aim is to organize the highand low flow speed in the inlet reasonably and to create a stable subsonic combustion zone in theentire Mach number range at the case of fixed geometry condition in which the stability of supersoniccombustion is assured and meanwhile to make sure the export flow remain dual-mode combustion.Based on the dual-mode combustion scramjet, two different hypersonic inlet modes, such asdirect export and hedging mode were designed. And comparison the similarities and differences ofthe two modes were made. The geometric parameters of the inlet which would influence theperformance of the inlet were investigated by numerical simulation. Analysis of characteristics andperformance parameters change of the inlet flow channel within the splitter plate was conducted andthe methods of inlet surface design and parameter selection recommendations was given.The hedging mode has advantages in the flow organization and structure dimensions, its internalflow field is more suitable for dual-mode combustion. Three-dimensional model selecting hedgingmode was designed, and studied its characteristics by numerical simulation and wind tunnelexperiment. Numerical investigation the starting characteristic, anti-pressure characteristics, speedcharacteristic and sideslip angle characteristics of the inlet were carried out. The results show thatperformance of the inlet can meet the design requirements, two-ducts flow distribution with thevariation of Mach number can meet the needs of dual-mode combustion.Experimental model was designed and wind tunnel tests were carried out in NHW wind tunnel ofNanjing University of Aeronautics and Astronautics. Test results agree well with numerical results,parameters consistent with the law of change which prove the correctness of the numerical method inthis paper. By numerical analysis and experimental research, the designed hypersonic inlet based ondual-mode combustion can meet the proposed requirements. Conclusions from this study have acertain reference value for the development of scramjet.