CAJ | 학술논문

文章在多块结构化框架下,采用面积加权平均的方法进行通量守恒传递,并成功地应用于存在"剪刀差"的全机增升装置复杂外形绕流N-S方程数值分析.通过对某民机全机低速构形所进行的气动力数值分析,计算结果与风洞实验结果吻合良好,表明该方法可以比较好地模拟如此复杂外形的流动细节,从而验证了文中所采用的面搭接多重网格技术、网格生成策略及流场计算方法的有效性.
문장재다괴결구화광가하,채용면적가권평균적방법진행통량수항전체,병성공지응용우존재"전도차"적전궤증승장치복잡외형요류N-S방정수치분석.통과대모민궤전궤저속구형소진행적기동력수치분석,계산결과여풍동실험결과문합량호,표명해방법가이비교호지모의여차복잡외형적류동세절,종이험증료문중소채용적면탑접다중망격기술、망격생성책략급류장계산방법적유효성.
Aim. The introduction of the full paper points out the urgent need for and the great difficulties involved in searching for the feasible method of CFD(computational fluid dynamics) simulation mentioned in the above title. We believe that our explorative efforts have resulted in a step forward. Section 1 briefs the usual method for the grid generation of 3D complex aircraft configuration. Section 2 uses the patched-grid technique, the third-order upwind-biased implicit flux-difference splitting (FDS) method and the implicit approximate factor decomposition method to discretize and solve the Navier-Stokes (N-S) equations. Section 3 uses the multi-grid technique to accelerate the convergence of the N-S equations. Section 4 presents and analyzes the calculation results in Figs. 6 and 7; the aerodynamic numerical analysis of the landing configuration and takeoff configuration of a certain aircraft with low Reynolds number shows preliminarily that our simulation method is indeed feasible for simulating the flow of very complex aircraft configuration.