摘要
为了更精确地将黏性干扰相关性理论应用到实际工程上,基于高超声速平板黏性干扰相关性理论和斜激波理论,针对当前广泛采用的黏性干扰相关性参数ν-′∞进行了修正,建立了气动力关联性更好的参数ν-″∞。采用计算流体力学(CFD)数值方法模拟了航天飞机轨道器外形OV-102在典型状态下的黏性干扰效应,考察了修正后黏性干扰相关性参数ν-″∞对于气动力数据的关联特性。验证结果表明:修正后的黏性干扰相关性参数ν-″∞对于黏性诱导的各气动力数据均有良好的关联特性,并且相比未修正的黏性干扰相关性参数ν-′∞更加有效。
In order to apply the viscous interaction correlation theory to engineering practice more precisely,the common viscous interaction correlation parameter ′ ∞ is corrected and a more correlative parameter ″ ∞ of aerodynamic forces is established based on the plane viscous interaction correlation theory and oblique shock wave theory at hypersonic velocity.The viscous interaction effect on OV-102 space shuttle under typical conditions is examined with numerical simulations by a computational fluid dynamics（CFD） method and the corrected viscous interaction correlation parameter ″ ∞ is examined for its correlativity with the aerodynamic force coefficients.The results show that the corrected viscous interaction correlation parameter ″ ∞ gives a good correlativity with all the aerodynamic force coefficients induced by viscosity and proves more effective than parameter ′ ∞.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2013年第7期1582-1587,共6页
Acta Aeronautica et Astronautica Sinica
基金
部级项目~~
关键词
高超声速
黏性干扰
航天飞机
相关性
气动力
计算流体力学
hypersonic
viscous interaction
space shuttle
correlation
aerodynamic force
computational fluid dynamics
