摘要
提出了高超声速面元法和热平衡参考温度法 ,给出了物体表面压强系数在不同情况下的计算公式。应用该方法对美国研制的天地往返运输器 ( X- 33)进行了气动力和气动加热特性计算。结果与试验数据吻合良好 ,证明该方法简捷、计算工作量小 。
An engineering computational method for the hypersonic aerodynamic properties of a full-reusable launch vehicle, such as pressure coefficients and aerodynamic coefficients, was presented. A computational model for the aerodynamic heating was also presented. U.S. X-33 was taken as a numerical example. The computed results for lift coefficients, drag coefficients and temperature distribution along centerline of windward side were given. It is shown that the computed results are consistent with the test data provided by sager.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2001年第2期205-208,共4页
Journal of Northwestern Polytechnical University
关键词
天地往返运输器
气动力
气动加热
工程计算
Aerodynamic heating
Aerodynamic loads
Aerodynamics
Aerospace vehicles
Supersonic aerodynamics
