SCHLIEREN STUDIES OF COMPRESSIBILITY EFFECTS ON DYNAMIC STALL OF TRANSIENTLY PITCHING AIRFOILS

被引：26

作者：

CHANDRASEKHARA, MS

AHMED, S

CARR, LW

机构：

[1] Naval Postgraduate School, Monterey, CA

[2] MCAT Institute, San Jose, CA

[3] NASA Ames Research Center, CA, 94035, Moffett Field

[4] Navy-NASA Joint Institute of Aeronautics, Department of Aeronautics and Astronautics

来源：

JOURNAL OF AIRCRAFT | 1993年 / 30卷 / 02期

关键词：

D O I：

10.2514/3.48268

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Compressibility effects on the flowfield of an airfoil executing rapid transient pitching motion from 0-60 deg over a wide range of Mach numbers and pitching rates were studied using a stroboscopic schlieren flow visualization technique. The studies have led to the first direct experimental documentation of multiple shocks on the airfoil upper surface flow for certain conditions. Also, at low Mach numbers, additional coherent vortical structures were found to be present along with the dynamic stall vortex, whereas at higher Mach numbers the flow was dominated by a single vortex. The delineating Mach number for significant compressibility effects was 0.3 and the dynamic stall process was accelerated by increasing the Mach number above that value. Increasing the pitch rate monotonically delayed stall to angles of attack as large as 27 deg.

引用

页码：213 / 220

页数：8

共 19 条

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