Research On The Design Method Of Wide-range Adjustable Internal Transfer Port

Hypersonic propulsion technology is the key to the development of hypersonic flight vehicle,and combined cycle engine is currently hypersonic propulsion technology research hot spot.So for TBCC inlet design study and from the flight within the scope of the numerical simulation to obtain the overall performance parameters of the inlet under modal is the primary work.This paper focuses on the rectangular inward turning inlet TBCC variable geometry inlet design.Firstly,Internal over-under dual-channel adjustable inward turning inlet were studied.The Mach number of transition level and the ramjet mode with over-under dual-channel adjustable inward turning aerodynamic model of the inlet of a variety of different design research,compare different inlet adjustment method for the influence of inlet adjustable period.Secondly,in this paper,by introducing a variable centrosome inward turning inlet design method with dual ramp for pre compression to increase the low Mach number of inward turning inlet working ability and overall performance parameters of the flow field.By changing the inward turning inlet throat area to expand the work of the converted inlet and the single channel adjustable inward turning inlet flow field numerical simulation is analyzed.Finally,this paper integrated use of a variety of design methods to improve the over-under dual-channel adjustable inward turning inlet aerodynamic profile design.For this model has carried on the full scope of work of flow field simulation,parallel double channel is obtained under different states adjustable inward turning overall performance parameters of the inlet.For transition mode to carry out the diversion ability of inlet under different deflection Angle model and the total pressure recovery were studied.