采用ICEM对某型民机着陆构型进行多块结构化点对点网格剖分,运用基于N-S方程的WISE MAN PLUS软件对该构型低速粘性复杂流场进行数值模拟。在进场条件下,计算的升力和试验值误差在3.8%以内,俯仰力矩和试验误差在3.6%以内;计算与试验失速...采用ICEM对某型民机着陆构型进行多块结构化点对点网格剖分,运用基于N-S方程的WISE MAN PLUS软件对该构型低速粘性复杂流场进行数值模拟。在进场条件下,计算的升力和试验值误差在3.8%以内,俯仰力矩和试验误差在3.6%以内;计算与试验失速迎角差别在1°左右,最大升力系数较试验小6.3%。同时还给出了一些流场显示结果,对复杂流场进行了机理分析。计算与风洞试验结果符合较好,满足工程需要。展开更多
This paper presents an investigation on the effect of probe support on the flow field of an axial compressor.The experiment is carried out in a large-scale low-speed research compressor.A cylindrical probe support int...This paper presents an investigation on the effect of probe support on the flow field of an axial compressor.The experiment is carried out in a large-scale low-speed research compressor.A cylindrical probe support intruding to 50% blade span was installed at 50% chord upstream from the rotor leading edge.The region from 5° to 32° off the probe support in the direction of rotation at the rotor outlet was measured with a 5-hole probe and a high-response total pressure probe.The experiment is performed at both near-design and near-stall points.The measuring results of 5-hole probe and high-response total pressure probe indicate that the probe blockage effect is different at different blade spans.The wake of the probe support weakens the leakage vortex intensity at the tip region,leading to greater total pressure rise.At near-design condition,the presence of probe support has a negative effect on the region from 75% to 92% span,while improves the flow field below 75% span.At near stall condition,the probe support has a negative effect on the region from 70% to 90% span,and almost has no influence on the flow field below 70% span.展开更多
文摘采用ICEM对某型民机着陆构型进行多块结构化点对点网格剖分,运用基于N-S方程的WISE MAN PLUS软件对该构型低速粘性复杂流场进行数值模拟。在进场条件下,计算的升力和试验值误差在3.8%以内,俯仰力矩和试验误差在3.6%以内;计算与试验失速迎角差别在1°左右,最大升力系数较试验小6.3%。同时还给出了一些流场显示结果,对复杂流场进行了机理分析。计算与风洞试验结果符合较好,满足工程需要。
基金funded by the National Natural Science Foundation of China,Grant No.51161130525,51136003,and the 111 Project,No.B07009
文摘This paper presents an investigation on the effect of probe support on the flow field of an axial compressor.The experiment is carried out in a large-scale low-speed research compressor.A cylindrical probe support intruding to 50% blade span was installed at 50% chord upstream from the rotor leading edge.The region from 5° to 32° off the probe support in the direction of rotation at the rotor outlet was measured with a 5-hole probe and a high-response total pressure probe.The experiment is performed at both near-design and near-stall points.The measuring results of 5-hole probe and high-response total pressure probe indicate that the probe blockage effect is different at different blade spans.The wake of the probe support weakens the leakage vortex intensity at the tip region,leading to greater total pressure rise.At near-design condition,the presence of probe support has a negative effect on the region from 75% to 92% span,while improves the flow field below 75% span.At near stall condition,the probe support has a negative effect on the region from 70% to 90% span,and almost has no influence on the flow field below 70% span.
