某型机机身前段安装大尺寸天线罩后的静压孔布局研究

The Research on the Static Hole Placement of an Aircraft with Large Radomes Installed on the Forward Fuselage

某型机在机身前段安装的大尺寸天线罩改变了机身压力分布,自身还产生了尾涡流。采用CFD和风洞试验方法研究表明天线罩使机身前段压力升高,天线罩前方可找到静压力系数接近0且随迎角和侧滑角变化很小的区域用于布置静压孔。测试发现天线罩尾流区内总压降低可达6%。机身前段的压力系数随着雷诺数增加有降低趋势。

The large radomes installed on the forward fuselage of an aircraft change the pressure distribution on the fuselage,and generate wake vortexes at the same time. CFD and wind tunnel tests reveal that the pressure on the forward fuselage is increased by the radomes. A location where the static pressure coefficient is close to 0 and varies slightly with changing angles of attack（ AOAs） and sideslipe angles can be found in front of the radomes,and is suitable to be selected as static hole. The tests show that the total pressure decreases as high as 6% with in the wake flow of the radomes. The pressure coefficient of the forward fuselage decreases with increasing Reynolds numbers.