CAJ | 학술논문

采用了一种基于多块网格的 N-S 方程和结构柔度影响系数法，考虑气动、结构非线性的基于 RBF 插值和RBF＆Delaunay 动网格变形技术的静气动弹性分析方法对喷流对弹性机翼的气动力影响进行了研究。利用 DLR F6翼身组合体构型对静气动弹性方法进行验证，保证了计算的可信性。采用该方法对比分析了某民用飞机无喷流／有喷流构型的静气动弹性特性，表明发动机喷流会给机翼带来一个正的扭转效应，抵消一部分机翼后掠效应的影响，使机翼前后缘挠度均会有所增大，弹性变形引起的多数剖面的附加扭转角有所减小。研究表明：喷流影响会使刚性机翼表面的压力分布发生变化，升力系数有所损失；考虑喷流的机翼静气动弹性变形是一个耦合效应，发动机喷流区主要受喷流影响，外翼段主要受弹性变形影响。数值模拟结果表明：无喷流影响时机翼的弹性变形使升力系数下降约16％，升阻比下降8．4％，考虑喷流影响时，升力系数下降达到18％，升阻比下降36％。因此，对于大展弦比机翼，考虑喷流影响的静气动弹性分析十分必要。
채용료일충기우다괴망격적 N-S 방정화결구유도영향계수법，고필기동、결구비선성적기우 RBF 삽치화RBF＆Delaunay 동망격변형기술적정기동탄성분석방법대분류대탄성궤익적기동력영향진행료연구。이용 DLR F6익신조합체구형대정기동탄성방법진행험증，보증료계산적가신성。채용해방법대비분석료모민용비궤무분류／유분류구형적정기동탄성특성，표명발동궤분류회급궤익대래일개정적뉴전효응，저소일부분궤익후략효응적영향，사궤익전후연뇨도균회유소증대，탄성변형인기적다수부면적부가뉴전각유소감소。연구표명：분류영향회사강성궤익표면적압력분포발생변화，승력계수유소손실；고필분류적궤익정기동탄성변형시일개우합효응，발동궤분류구주요수분류영향，외익단주요수탄성변형영향。수치모의결과표명：무분류영향시궤익적탄성변형사승력계수하강약16％，승조비하강8．4％，고필분류영향시，승력계수하강체도18％，승조비하강36％。인차，대우대전현비궤익，고필분류영향적정기동탄성분석십분필요。
Based on the N-S equations of multi-block structural grid and the method of structure flexibility coefficient matrix,an approach to CFD/CSD non-linear coupling problem based on ra-dial basis functions(RBF)interpolation technology is established,RBF&Delaunay mesh motion method is adopted,which is used to compute the non-linear aeroelasticity of flexible aircraft with high aspect radio.This method is validated using DLR F6 configuration simulation.According to this method,static aeroelasficities of a civil aircraft under no jet/jet condition are investigated, showing that the engine jet can make wing plus twist,which is weaken wing sweepback effect, then the leading and trailing edge bending deformation increase and most of the favorable current profile twist angles decrease.Studies show that under the powered condition,the pressure distri-bution of rigid wing is changed,its lift confficient is reduced.The static aeroelastic deformation is a coupling effect,where the engine jet region is mainly influenced by jet while the outer wing is mainly by elastic deformation.The result of numerical simulation demonstrates that considering the aeroelasticity effect for no jet condition,the lift coefficient decreases by about 16% and the lift drag radio decreases by 8.4%.Whereas for powered case,the lift coefficient decreases by 18%,the lift drag radio decreases by 36%.Therefore,it is necessary to analyze static aeroelas-ticity of high aspect radio civil aircraft under powered condition.