航空学报2026，Vol.47Issue(5)：70-88,19.DOI:10.7527/S1000-6893.2026.32462
高速飞行器质量引射条件下气动热数值计算
Numerical computation on aerothermal environment with mass injection for high-speed aircraft
摘要
Abstract
Proper understanding and evaluation of the aerothermal environment with mass injection for high-speed air-craft are prerequisites to develop corresponding thermal protection technology.To address the prediction of aerother-mal environment with mass injection,the numerical simulation method of mass injection is proposed and verified in high-temperature nonequilibrium flow.Subsequently,a modified heat flux characterization formula is theoretically de-rived considering comprehensive wall effects,including catalysis,ablation,pyrolysis and active injection.The new characterization method and heat reduction mechanisms are numerically investigated using a blunt wedge configura-tion in typical flight states.The results demonstrate the following:using the heat flux ultimately experienced by the ve-hicle structure as the criterion for wall heat flux assessment aligns with traditional wall heat flux formula while also pro-viding a reasonable evaluation of heat flux with complex wall effects.Conventional heat flux formula needs to be cor-rected since it overestimates wall heat flux and underestimates cooling efficiency when evaluating the thermal reduction effect of mass injection.The corrected heat flux expression under mass injection conditions includes heat conduction from flow field,heat absorption/release from wall reactions,and formation enthalpy of injected media,degenerating into the traditional heat flux expression in non-ablative and non-injection conditions.For non-catalytic,non-ablative and active injection wall,heat flux consists solely of conductive heat flux.As a result,cooling effect of active injection is achieved by significantly reducing the normal temperature gradient at the wall.The cooling efficiency is further im-proved while incorporating the enthalpy of injected water vapor,but the dominant factor remains the reduction of con-ductive heat flux.关键词
质量引射/气动热/非平衡/催化/烧蚀/高速飞行器Key words
mass injection/aerothermal/nonequilibrium/catalysis/ablation/high-speed aircraft分类
航空航天引用本文复制引用
刘庆宗,丁明松,董维中,孔文慧,江涛..高速飞行器质量引射条件下气动热数值计算[J].航空学报,2026,47(5):70-88,19.基金项目
国家数值风洞工程 National Numerical Windtunnel Project （）
