CAJ | 학술논문

为了提高机翼等飞行器部件在粘性绕流下的气动力预测精度，研究了在非结构RANS求解器中耦合转捩预测的方法。以求解三维ONERA M6机翼的转捩点位置及气动力特性为例，求解过程为：先将RANS方程求解得到的机翼表面压力分布作为层流边界层方程求解的输入参数；然后采用eN-Database转捩预测方法分析层流边界层方程求解得到的边界层内相关参数，并得到机翼的转捩点位置；最后将转捩点位置传回RANS求解器中，重新进行流场计算得到考虑转捩后的气动力特性。使用上述方法计算出的结果与实验值吻合较好，验证了程序的有效性。
위료제고궤익등비행기부건재점성요류하적기동력예측정도，연구료재비결구RANS구해기중우합전렬예측적방법。이구해삼유ONERA M6궤익적전렬점위치급기동력특성위례，구해과정위：선장RANS방정구해득도적궤익표면압력분포작위층류변계층방정구해적수입삼수；연후채용eN-Database전렬예측방법분석층류변계층방정구해득도적변계층내상관삼수，병득도궤익적전렬점위치；최후장전렬점위치전회RANS구해기중，중신진행류장계산득도고필전렬후적기동력특성。사용상술방법계산출적결과여실험치문합교호，험증료정서적유효성。
In order to improve prediction accuracy of aerodynamic configurations,this paper studies the eN-Database transition prediction method coupled with an unstructured RANS solver. In the case of 3D ONERA M6 wing,the surface pressure coefficients computed by an unstructured RANS solver are transferred to boundary layer equations solver to gain velocity profile and other necessary information,then the eN-Data-base predicts transition locations of the wing,as the feedback to the RANS solver to gain more accurate flow field information. Good agreement between computational and experimental transition locations,forces and pressure distributions verifies the validity of method developed in this paper.