中国航空学报（英文版）
中國航空學報（英文版）
중국항공학보（영문판）
CHINESE JOURNAL OF AERONAUTICS
2006年
4期
304-308
,共5页
邓有奇%马明生%郑鸣%周乃春
鄧有奇%馬明生%鄭鳴%週迺春
산유기%마명생%정명%주내춘
计算流体力学%定常流N-S方程%结构非结构混合网格%有限体积法%栅格翼导弹
計算流體力學%定常流N-S方程%結構非結構混閤網格%有限體積法%柵格翼導彈
계산류체역학%정상류N-S방정%결구비결구혼합망격%유한체적법%책격익도탄
computational fluid dynamics%steady flow%Navier-Stokes equation%hybrid structure-unstructured grid%finite volume%grid fin missile
采用结构和非结构混合网格技术,对栅格翼导弹黏性流场进行数值模拟,预测其气动特性.计算的马赫数为0.7～2.5.用有限体积法和LU-SGS算法求解N-S方程.计算与实验数据以及栅格翼附近流场结构进行了比较.
採用結構和非結構混閤網格技術,對柵格翼導彈黏性流場進行數值模擬,預測其氣動特性.計算的馬赫數為0.7～2.5.用有限體積法和LU-SGS算法求解N-S方程.計算與實驗數據以及柵格翼附近流場結構進行瞭比較.
채용결구화비결구혼합망격기술,대책격익도탄점성류장진행수치모의,예측기기동특성.계산적마혁수위0.7～2.5.용유한체적법화LU-SGS산법구해N-S방정.계산여실험수거이급책격익부근류장결구진행료비교.
Viscous CFD computations are performed to predict the aerodynamic coefficients and flowfield for a missile with grid fins by using hybrid structure-unstructured grids. The computations are made at Mach numbers of 0.7 and 2.0. Full N-S equations are discretized into finite volume form and solved by an algorithm in LU-SGS. The comparisons between computation and experimental data are made, and the detailed flow structure near grid fin is shown and examined.
