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An experiment of a hypersonic vehicle configuration was conducted.The pressure difference of forbody precompress surface is small.Pressure difference of three monitor points are 25.2%,20.5% and 17.29% respectively in the design condition.It indicates that there is crosswise flow in forebody boundary layer.Pressure difference at Ma=6.971 is lower than those of two other Mach number conditions.It indicates that the tested configuration has good aerodynamic performance in high Mach number.Angle of attack has no great influence on the pressure difference.In almost all the angle of attack conditions,the pressure difference at Ma=6.971 is slightly smaller than that in Ma=5.993.The difference in the third precompress surface is slightly smaller than those in two others.
An experiment of a hypersonic vehicle configuration was conducted. The pressure difference of forbody precompress surface is small. Pressure difference of three monitor points are 25.2%, 20.5% and 17.29% respectively in the design condition. It means that there is crosswise flow in forebody boundary layer. Stress difference at Ma = 6.971 is lower than those of two other Mach number conditions. It means that the tested configuration has good aerodynamic performance in high Mach number. Angle of attack has no great influence on the pressure difference ..In almost all the angle of attack conditions, the pressure difference at Ma = 6.971 is slightly smaller than that in Ma = 5.993. The difference in the third precompress surface is slightly smaller than those in two others.