摘要
建立了将合成射流激励器腔体、出口喉道、外部流场作为单连域计算处理的吹/吸型边界模型。在此基础上,对横向主流偏转角及上下壁面压力变化进行了讨论。计算结果表明,激励器布置位置是影响主流偏转角的重要因素,在主流通道内侧,激励器与主流出口之间的上下壁面压力差较大。文中还对两种不同模式下合成射流对主流的控制效果做了比较。
Modeling a blowing/suction type boundary for synthetic jet actuator, it considers the actuator cavity, exit nozzle and exterior flow field as a single computational region. Then the vectoring angle of the across primary jet and the different pressure on each wall are discussed. It shows that the vectoring angle of the across primary jet is affected mainly by the locations of actuator, and in the primary jet channels the pressure difference on the walls between actuator and exit of primary jet is especially great. The synthetic jet＇s effect on primary jet under different mode is discussed in the paper.
出处
《空气动力学学报》
EI
CSCD
北大核心
2007年第1期92-96,共5页
Acta Aerodynamica Sinica
基金
国家自然科学基金资助项目(批准号:50176055)
国家自然科学基金重大研究计划资助项目(批准号:90205016)
关键词
激励器
模式
合成射流
数值模拟
横向主流
actuator
mode
synthetic jet
numerical simulation
across primary jet
