Aeroheating experiment research on hypersonic integrated vehicle forebody/ramjet

A scramjet-powered aircraft,due to the increase in speed,aeroheating is very serious.Moreover,high flighting Mach number makes higher stagnation temperature within the ramjet combustor.In this text,heat flux measurements were conducted through wind tunnel experiments using platinum film resistance thermometer measurement technology,and experiment mach number is M=6.4 and M=4.0.Experiment results were presented about heat flux distribution on forebody,strut and flow path,which were used to study effects of boundary flow regime,suction and shockwave reflection on heat flux distribution.Results show that boundary layer flow regime has significant impact on heat flux distribution,and heat flux value of turbulence at ramp is about 3.3 times of laminar value.Boundary layer suction experiment reveals that suction increases rate of flux.Heat flux distribution and flow study show that shockwave heating and reflection markedly influence heat flux distribution,and high Mach number produces more serious shockwave heating.