Aerothermodynamic Testing of the Crew Exploration Vehicle at Mach 6 and Mach 10
Aerothermodynamic Testing of the Crew Exploration Vehicle at Mach 6 and Mach 10
复制标题
载人探索飞行器 6 马赫和 10 马赫的空气热动力测试
DOI：
10.2514/1.39247
复制
发表时间：
2009
影响因子：
1.6
通讯作者：
K. Berger
中科院分区：
文献类型：
--
作者：
K. Berger
An experimental wind-tunnel program is being conducted in support of a NASA wide effort to develop a Space Shuttle replacement and to support the agency’s long-term objective of returning to the moon andMars. This paper documents experimentalmeasurementsmade on several scaled ceramic heat transfermodels of the proposedProject Orion Crew Exploration Vehicle. The experimental data highlighted in this paper will be used to assess numerical tools thatwill be used to generate theflight aerothermodynamic database. Global heat transfer images and centerline heat transfer distributions were obtained over a range of freestreamReynolds numbers and angles of attackwith the phosphor thermography technique. Temperature dataweremeasured on the forebody and afterbody andwere used to compute the heating on the vehicle as well as the boundary-layer state on the forebody surface. Several model support configurations were assessed to minimize potential aftbody support interference. Although naturally fully developed turbulent levels were not obtained on the forebody, the use of boundary-layer trips generated fully developed turbulent flow. Laminar and turbulent computational results are shown to be in good agreement with the data. In addition, the ability of the global phosphor thermography method to provide quantitative heating measurements in the low-temperature environment of the capsule base regionwas assessed and the lack of significant model support hardware influence on heating was shown.
