SKIN-FRICTION MEASUREMENTS IN 3-DIMENSIONAL, SUPERSONIC SHOCK-WAVE BOUNDARY-LAYER INTERACTION

被引：11

作者：

WIDEMAN, JK

BROWN, JL

MILES, JB

OZCAN, O

机构：

[1] NASA,AMES RES CTR,MOLELING & EXPTL VALIDAT BRANCH,MOFFETT FIELD,CA 94035

[2] ISTANBUL TECH UNIV,DEPT AERONAUT & ASTRONAUT,ISTANBUL 80626,TURKEY

来源：

AIAA JOURNAL | 1995年 / 33卷 / 05期

关键词：

D O I：

10.2514/3.12503

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The experimental documentation of a three-dimensional shock-wave/boundary-layer interaction in a nominal Mach 3 flow is presented. The model consisted of a sting-supported cylinder, aligned with the freestream flow, and a 20-deg half-angle conical hare offset 1.27 cm from the cylinder centerline. Surface oil flow, laser light sheet illumination, and spark schlieren photography were used to document the now topology. Extensive surface-pressure and skin-friction measurements were made throughout the interaction region. A laser interferometric skin-friction instrument was employed to acquire the skin-friction data. Resolved skin-friction measurements of C-fx and C-fz were made within the highly swept three-dimensional separated regions. The skin-friction data will be of particular value for turbulence modeling and computational fluid dynamics validation.

引用

页码：805 / 811

页数：7

共 21 条

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