Transonic shock oscillations on NACA0012 aerofoil

被引：11
|
作者：
Raghunathan, S [1 ]
Mitchell, RD [1 ]
Gillan, MA [1 ]
机构：
[1] Queens Univ Belfast, Dept Aeronaut Engn, Belfast, Antrim, North Ireland
来源：
SHOCK WAVES | 1998年 / 8卷 / 04期
关键词：
unsteady aerodynamics; shock oscillations; transonic flows; buffet;
D O I：
10.1007/s001930050113
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
The mechanism of the origin of shock oscillations on NACA0012 aerofoils is investigated using a moving grid thin layer Navier Stokes code. The method used to understand the mechanism is to initiate the shock oscillations on an aerofoil by moving the aerofoil from a regime of steady transonic flow into a regime of periodic flow by a change in airflow incidence. The results indicate that the shock induced bubble plays a leading role in the origin of shock oscillations and the trailing edge has an affect on its amplitude.
引用
收藏
页码：191 / 202
页数：12
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