计算物理
計算物理
계산물리
CHINESE JOURNAL OF COMPUTATIONAL PHYSICS
2010年
1期
59-64
,共6页
稀薄气体效应%DSMC%尖前缘%高超声速
稀薄氣體效應%DSMC%尖前緣%高超聲速
희박기체효응%DSMC%첨전연%고초성속
rarefied gas effect%DSMC%sharp leading-edge%hypersonic
以微钝尖锥为飞行器前缘模型,采用基于分子运动论的DSMC方法模拟不同前缘曲率半径的尖锥在高超声速来流下的气动热环境,计算驻点热流率,并与Fay-Riddell公式和其他修正理论作对比,研究具有局部稀薄气体效应的高超声速尖锥气动加热特征及其变化规律.发现修正的Cheng参数适合作为工程上判断驻点区域稀薄气体效应影响大小的判据.
以微鈍尖錐為飛行器前緣模型,採用基于分子運動論的DSMC方法模擬不同前緣麯率半徑的尖錐在高超聲速來流下的氣動熱環境,計算駐點熱流率,併與Fay-Riddell公式和其他脩正理論作對比,研究具有跼部稀薄氣體效應的高超聲速尖錐氣動加熱特徵及其變化規律.髮現脩正的Cheng參數適閤作為工程上判斷駐點區域稀薄氣體效應影響大小的判據.
이미둔첨추위비행기전연모형,채용기우분자운동론적DSMC방법모의불동전연곡솔반경적첨추재고초성속래류하적기동열배경,계산주점열류솔,병여Fay-Riddell공식화기타수정이론작대비,연구구유국부희박기체효응적고초성속첨추기동가열특정급기변화규률.발현수정적Cheng삼수괄합작위공정상판단주점구역희박기체효응영향대소적판거.
A small nose sphere-cone is taken as vehicles leading-edge,and kinetic-theory based DSMC method is used to simulate aerothermal environment of hypersonic sphere-cone with different nose radii.Stagnation point heat fluxes calculated by DSMC are compared with that by Fay-Riddell formulae and other theories.Aerothermodynamic characteristics of hypersonic small nose cone with local rarefied gas effect are studied.It is found that the modified Cheng's parameter is a credible criterion in predicting rarefied gas effects at stagnation point of sharp leading-edges.
