哈尔滨商业大学学报(自然科学版)
哈爾濱商業大學學報(自然科學版)
합이빈상업대학학보(자연과학판)
JOURNAL OF HARBIN UNIVERSITY OF COMMERCE(NATURAL SCIENCES EDITION)
2015年
1期
69-72
,共4页
侧向喷流%干扰%超声速%数值模拟%喷口位置
側嚮噴流%榦擾%超聲速%數值模擬%噴口位置
측향분류%간우%초성속%수치모의%분구위치
lateral jet%interaction%supersonic%numerical simulation%jet position
通过求解三维N-S可压缩方程,对弹-翼组合体的侧向喷流流场进行数值模拟。研究了不同喷口位置,不同喷流压力下的干扰流场。分析了流场结构,研究了流场干扰与气动力干扰的关系。结果表明,在超音速流场中,喷口位置的不同,会带来喷流放大因子的变化。喷口位置相对于翼偏转,即喷口与翼面的夹角增大,喷流放大因子相应增加,侧向喷流的控制效果更好。
通過求解三維N-S可壓縮方程,對彈-翼組閤體的側嚮噴流流場進行數值模擬。研究瞭不同噴口位置,不同噴流壓力下的榦擾流場。分析瞭流場結構,研究瞭流場榦擾與氣動力榦擾的關繫。結果錶明,在超音速流場中,噴口位置的不同,會帶來噴流放大因子的變化。噴口位置相對于翼偏轉,即噴口與翼麵的夾角增大,噴流放大因子相應增加,側嚮噴流的控製效果更好。
통과구해삼유N-S가압축방정,대탄-익조합체적측향분류류장진행수치모의。연구료불동분구위치,불동분류압력하적간우류장。분석료류장결구,연구료류장간우여기동력간우적관계。결과표명,재초음속류장중,분구위치적불동,회대래분류방대인자적변화。분구위치상대우익편전,즉분구여익면적협각증대,분류방대인자상응증가,측향분류적공제효과경호。
By solving the 3D compressible N-S equations, a numerical simulation of bomb-wing combination was discussed.The flow field with different jet position and different pressure ratio was researched.The flow field structure was analyzed, and the relations be-tween field interference and aerodynamic interference were studied.The results showed that in the supersonic flow field, different jet positions will bring jets zoom factor changes.With the increase of the angle between the jet position and the wing surface, the jet controlling be-comes more effective.