摘要
试验在某型飞机上进行,飞机进气锥按Ma数变化进行无级调节,进气道两侧距唇口约1.5m处各有一放气门,距唇口约5.7m处各有一风戽式辅助进气门(Ma>1.4自动关闭)。 为了测取左进气道出口总压和流场图谱,在压气机进口装有一米字耙,每支耙上有六个按等环面分布的总压测点,在壁面上有四个均匀分布的静压测点。 试飞由DAM-Ⅲ磁记录系统记录,经电子计算机处理。
A flight-test study on the total pressure recovery and the exit flow field in an inlet of a supersonic jet aircraft is presented. The total pressure recoverycharacteristics and the exit total pressure distortion patterns in the transonic flight are given. The variation of the total pressure recovery coefficient andthe distortion factor with Mach number during inlet-engine matching is illustra-ted. The flighttest study provides valuable data for research on inlet-engine compatibility .
出处
《航空动力学报》
EI
CAS
1986年第2期154-156,188-189,共5页
Journal of Aerospace Power
