类X-51A飞行器巡航状态气动与燃烧流场特性分析

Analysis of Aerodynamic and Combustion Field Characteristics of X-51A Type HypersonicVehicle under Cruise State

摘要:

以类X-51A 高超声速飞行器为研究对象,重构了其机体外形及内部超燃冲压发动机的一体化模型,并通过数值方法研究了该目标巡航状态下的气动与燃烧耦合流场特性。数值分析结果表明:类X-51A 飞行器高压区主要集中在机体头部、进气道压缩段、进气道入口侧壁及尾翼前缘,且内部燃烧室的总体压力显著高于机体表面的;燃烧室内靠近两侧壁面的喷孔燃料喷注深度高于中间喷孔的,下游喷孔喷注深度高于上游喷孔的,凹腔附近喷孔喷注深度高于无稳焰结构的壁面喷孔的;燃烧产物羽流长度超过50 m,且持续向机体上方发生偏移。计算结果可为类X-51A 及相关飞行器红外探测与目标识别等技术提供流场数据参考。

Abstract:

The X-51A type hypersonic vehicle was taken as the research object,anintegrated model of the body shape and internal scramjet was reconstructed.The aerodynamicand combustion coupled flow field characteristics of the X-51A type hypersonic vehicle undercruise state were studied using numerical methods.The results of numerical analysis showthat the high pressure regions of the X-51A type hypersonic vehicle are mainly concentratedin the body head,the inlet compression section,the inlet sidewall,the leading edge of the tailwing,the overall pressure of the internal combustion chamber is significantly higher than that of the body surface;the injection depth of fuel nozzle near the two sides of the wall in thecombustion chamber is higher than that of the middle fuel nozzle,the injection depth of thedownstream fuel nozzle is higher than that of the upstream fuel nozzle,the injection depth ofthe fuel nozzle near the cavity is higher than that of the fuel nozzle on the wall without flamestability structure;the length of the combustion product wake exceeds 50 m,it continues toshift to the upper part of the aircraft.The calculation can provide flow field data reference fortechnologies such as infrared detection and target recognition of X-51A and related aircraft