Transonic shock oscillations on NACA0012 aerofoil

被引：16

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

页码：191 / 202

页数：12

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