UNSTEADY PRESSURE MEASUREMENTS ON A BICONVEX AIRFOIL IN A TRANSONIC OSCILLATING CASCADE.

被引：0

作者：

Shaw, L.M. ^{[1
]}

Boldman, D.R. ^{[1
]}

Buggele, A.E. ^{[1
]}

Buffum, D.H. ^{[1
]}

机构：

[1] NASA, Lewis Research Cent,, Cleveland, OH, USA, NASA, Lewis Research Cent, Cleveland, OH, USA

来源：

Journal of Engineering for Gas Turbines and Power | 1986年 / 108卷 / 01期

关键词：

PRESSURE MEASUREMENT;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

Flush-mounted dynamic pressure transducers were installed on the center airfoil of a transonic oscillating cascade to measure the unsteady aerodynamic response as nine airfoils were simultaneously driven to provide 1. 2 deg of pitching motion about the midchord. Initial tests were performed at an incidence angle of 0. 0 deg and a Mach number of 0. 65 in order to obtain results in a shock-free compressible flow field. Subsequent tests were performed at an angle of attack of 7. 0 deg and a Mach number of 0. 80 in order to observe the surface pressure response with an oscillating shock near the leading edge of the airfoil.

引用

页码：53 / 59

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