CAJ | 학술논문

本文利用二维雷诺平均的Navier-Stokes方程，采用K-ε湍流模式，运用有限体积法，对大型运载火箭的助推器与芯级的激波边界层干扰进行了二维数值模拟.数值结果表明在助推器激波的干扰下，芯级边界层流场明显出现了分离和再附过程。助推器头部形状对流场有显著的影响，在半球助推器头形状情形下由于产生丁较强的弓形激波，边界层的分离和再附过程最显著，压力分布最复杂。助推器与芯级距离对流场也有显著的影响，距离较小时，压力系数较大，激波边界层的强干扰会产生分离区甚至分离泡。
본문이용이유뢰낙평균적Navier-Stokes방정，채용K-ε단류모식，운용유한체적법，대대형운재화전적조추기여심급적격 파변계층간우진행료이유수치모의.수치결과표명재조추기격파적간우하，심급변계층류장명현출현료분리화재부과정。조추기두 부형상대류장유현저적영향，재반구조추기두형상정형하유우산생정교강적궁형격파，변계층적분리화재부과정최현저，압력분포 최복잡。조추기여심급거리대류장야유현저적영향，거리교소시，압력계수교대，격파변계층적강간우회산생분리구심지분리포。
A two-dimensional Reynolds-averaged Navier-Stokes solver is applied to analyze the aerodynamic behavior of the ShockBoundary-Layer interaction of rocket with a booster. The K- ε turbulence model and a finite volume method in a unstructured body-fitted curvilinear coordinates have been used. The results indicate that the separation and the reattachment occur in the Boundary-Layer of the main rocket because of the shock interaction. The shape of the booster nose affects the flow field obviously. In the case of the hemisphere booster nose the pressure has complicate distributions and the separation is very clear. The distance between the booster and main rocket has the evident effect on the flow field. If the distance is smaller, the pressure coefficient is bigger, the separation zone even the separation bubble occurs.