摘要
建立了激波/边界层干扰脉动压力测试系统。对一组后掠压缩角产生的激波/边界层干扰脉动压力流场进行测量,结果表明,脉动压力时均值及其分布与静态测量得到的结果一致。测量还发现在实验的锥形干扰范围内。
A fluctuating wall-pressure measurement system is established. In a conical interaction flowfield produced by a set of swept compression corners, the measurement results show that the RMS value of fluctuating pressure and its distributions are consistent with those measured by static pressure measurement system (with Scani probe). The intermittent phenomenon caused by oscillating shock wave at relatively low frequencies did not appear obviously within the whole test region, which is different from the results in two dimensional conditions.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第3期344-347,共4页
Acta Aeronautica et Astronautica Sinica
关键词
激波
边界层
干扰
压力振荡
测量
shock waves, boundary layer, interference, pressure oscillations, measurement