Aeroheating analysis of propulsion/forebody integration has been conducted by means of CFD technique.Especially

different computation models are adopted for different flow regime

including laminar

transition and turbulent flow.In this text

compressibility-corrected SSGZ-J k-ε model has been employed in turbulent region

moreover

we introduce algebraic intermittency model of transition to simulate the transition process from laminar to turbulent.By these methods

wall heat flux of forebody and engine has been calculated and compared with experimental results.Results show that compressibility-corrected SSGZ-J kε model can reasonably predict heat flux in the complex high-speed compressible flow

and algebraic intermittency model of transition can simulate transition process of boundary layer.Flow regime

structure geometry and shock wave have great effects on heat flux.