摘要
为了评估飞行攻角和侧滑角快速变化对进气道出口畸变、发动机稳定性的影响,进行了某型飞机高机动下进气道/发动机相容性飞行试验,获得了快速飞行姿态改变时进气道与发动机相关参数的试验数据.通过对飞行数据的整理、计算和分析,研究了高机动状态下进气道出口的畸变特性、发动机稳定性以及进气道出口畸变和发动机稳定性的相关性.研究结果表明:高机动飞行状态下进气道出口流场品质变差,发动机稳定性变差.
The test of inlet/engine compatibility was carried out during aircraft maneuvers with rapidly changing angle-of-attack（AOA）,angle-of-sideslip（AOSS）.The same important test data about inlet/engine compatibility by flightting test were acquired.The test data were selected,calculated and analyzed,and at last the relation among rapidly changing aircraft maneuvers,inlet total pressure distortion and the stability of engine,as well as the relation between inlet total pressure distortion and the stability of engine were obtained.It shows that,the stability of engine and inlet total pressure distortion become worse due to rapidly changing aircraft maneuvers.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第9期2077-2082,共6页
Journal of Aerospace Power
基金
"十一.五"预研航空支撑项目
关键词
飞行试验
飞行攻角
飞行侧滑角
综合压力畸变
稳定性
flightting test angle-of-attack angle-of-sideslip inlet total pressure stability
