摘要
火箭羽流会造成噪声、烟雾、热辐射、环境污染和信号衰减等多种效应 ,因此研究排气羽流问题至关重要。采用三维隐式有限体积TVD格式 ,通过求解定常可压缩Euler方程 ,数值模拟了来流马赫数为 1 0、1 5、2 0和喷管出口压力比为1 0、2 0、3 0时的火箭羽流场 ,并对各流场参数和噪声进行了计算和比较。所采用的二阶格式具有分辨率高、收敛快速稳定、可较好模拟复杂计算区域和流场波系等优点。声压级在相交激波点附近出现剧烈变化 ,喷管出口处的激波和排气羽流造成强噪声。
The rocket exhaust plume causes the effects of noise,smoke,flame and heat radiation,environment pollution and signal attenuation,etc.So it is important to study exhaust plume.An implicit TVD finite volume scheme was used to compute the steady state,compressible,three dimensional flow field over the rocket at Mach 1.0,1.5,2.0 flight condition with nozzle pressure ratio 1.0,2.0,3.0.The pressure,density and Mach number were computed and compared for all the cases,noise was predicted using the acquired variation of pressure.The second order scheme used by the paper has advantages of high shock resolution,rapid and steady convergence,simulating complex shape and flow field,etc.The solutions clearly present the flow field phenomena,structure,and features.The sound pressure level changes acutely in shock intersection,and shocks outside nozzle and exhaust plume cause strong noise.
出处
《南京理工大学学报》
EI
CAS
CSCD
2000年第6期519-522,539,共5页
Journal of Nanjing University of Science and Technology
