CALCULATION OF LOW REYNOLDS-NUMBER FLOWS AT HIGH ANGLES OF ATTACK

被引：2

作者：

CEBECI, T

MCILVAINE, M

CHEN, HH

LIEBECK, RH

机构：

[1] California State University, Long Beach, CA

[2] Douglas Aircraft Company, Long Beach, CA

来源：

JOURNAL OF AIRCRAFT | 1991年 / 28卷 / 04期

关键词：

D O I：

10.2514/3.46019

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Calculated results are reported for Eppler and Liebeck airfoils with chord Reynolds numbers ranging from 10(5) to 5 x 10(5) and for angles of attack up to stall. They were obtained with an interactive finite-difference boundary-layer method in which the turbulence model employs an extended intermittency expression in the Cebeci and Smith eddy-viscosity model and the location of the onset of transition is determined from linear-stability theory. Comparisons with experiments indicate agreement within measurement uncertainty, except at stall conditions, and close correspondence with the ISES code, which is based on the solution of integral equations.

引用

页码：246 / 252

页数：7

共 27 条

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