实验流体力学2017，Vol.31Issue(1)：13-19,7.DOI:10.11729/syltlx20160084
比热比和压比对高超飞行器尾喷流影响的实验研究
Experimental study of the influence of the specific heat and pressure ratios on the hypersonic vehicle’s nozzle plume
贺旭照 1秦思 1周凯 1乐嘉陵1
作者信息
- 1. 中国空气动力研究与发展中心超高速空气动力学研究所 高超声速冲压发动机技术重点实验室，四川 绵阳 621000
- 折叠
摘要
Abstract
The experimental studies have been carried out to explore the influences of the Spe-cific Heat Ratio(SHR)on the air-breathing hypersonic vehicle’s nozzle plume at CARDC’s 0.5m hypersonic wind tunnel.The SHR of the plume at the scramjet exit is simulated by CF4+Air with SHR=1.25.The Laval nozzle is used in the experimental model to generate the supersonic nozzle plume and the flow field generated by the wind tunnel is used to simulate the model’s ex-ternal flow field.The differences of the pressure distributions and flow field structures are com-pared between the pure air and mixture gas plumes.Results show that in the mixture gas plume, the pressure distributions are higher than air plume in the core and interaction regions.The SHR is one of the key parameters for the study of air-breathing hypersonic vehicle’s plume.关键词
高超声速飞行器/比热比/四氟化碳/测压实验/喷流Key words
hypersonic vehicle/specific heat ratio/CF4/pressure test experiment/plume分类
航空航天引用本文复制引用
贺旭照,秦思,周凯,乐嘉陵..比热比和压比对高超飞行器尾喷流影响的实验研究[J].实验流体力学,2017,31(1):13-19,7.
