方案详情文
This research project examines supersonic jets from nozzles representative of the practical variable-geometry convergent-divergent nozzles used on high-performance military aircraft. The nozzles employed have conical convergent sections, sharp throats and conical divergent sections. Nozzles with design Mach numbers of 1.3, 1.5, 1.56 and 1.65 are tested and the flow and acoustics examined. Such nozzles are found to produce a double-diamond shock structure consisting of two overlapping sets of shock cells, one cast from the nozzle lip and one cast from the nozzle throat. These nozzles are found to produce no shock-free condition at or near the design condition. As a result they produce shockassociated noise at all supersonic conditions. The shock cell spacing, broad-band shock-associated noise peak frequency and screech frequency all match those of more traditional nearly isentropic convergentdivergent
nozzles.
智能文字提取功能测试中
关闭产品配置单
北京欧兰科技发展有限公司为您提供《飞机喷嘴中喷嘴喷射的流动和声学研究检测方案(粒子图像测速)》，该方案主要用于军工中喷嘴喷射的流动和声学研究检测，参考标准《暂无》，《飞机喷嘴中喷嘴喷射的流动和声学研究检测方案(粒子图像测速)》用到的仪器有德国LaVision PIV/PLIF粒子成像测速场仪。
我要纠错
推荐专场
相关方案
咨询
