CAJ | 학술논문

使用Fastran软件仿真，采用多块结构网格Roe差分分裂格式求解雷诺平均N-S方程，数值模拟了高超声速情况下火箭助推器头部三维激波在芯级上产生的激波反射和激波边界层干扰流场。通过与典型算例和风洞实验结果的比对，特性符合规律，满足工程计算的精度要求，结果清晰地反映了流场结构以及局部气动载荷的分布。通过改变头锥形状，分析了新一代运载火箭斜头形助推器产生气动干扰的特性，并与目前使用的直头形助推器作比较，指出两者构型上的差别对芯级与助推器间气动干扰的影响，对未来捆绑火箭气动特性有一定预示意义。
사용Fastran연건방진，채용다괴결구망격Roe차분분렬격식구해뢰낙평균N-S방정，수치모의료고초성속정황하화전조추기두부삼유격파재심급상산생적격파반사화격파변계층간우류장。통과여전형산례화풍동실험결과적비대，특성부합규률，만족공정계산적정도요구，결과청석지반영료류장결구이급국부기동재하적분포。통과개변두추형상，분석료신일대운재화전사두형조추기산생기동간우적특성，병여목전사용적직두형조추기작비교，지출량자구형상적차별대심급여조추기간기동간우적영향，대미래곤방화전기동특성유일정예시의의。
The reynolds-averaged Navier-Stokes equations are solved numerically by Roe second-order flux difference splitting schemes by using CFD fastran solver. Thus a numerical study is made for supersonic flow between a rocket and a booster’s nosecone with shock reflection and shock-boundary layer interaction. The computed results display flow structure in detail and the pressure distributions on the surface show good agreement with the data in experiments and references. A simulation on another configuration with oblique cone used in the next generation rockets is also made to have a compare and bring directive significance on aerodynamic character for future binding rocket.