CAJ | 학술논문

为解决航空器结构变形问题，在研究相关非定常流场基础上，建立了包含结构变形的非定常流场数值求解方法，运用无限插值法（ TFI）生成任意时刻的非定常动态网格，通过与刚性动网格比较，证明了方法的可行性，并以NACA0012翼型为算例，对翼型俯仰振荡运动中表面柔性变形问题进行了数值模拟，发现俯仰振荡中叠加变形形式为一阶振型时，可以明显地提高升力、增加动稳定、提高升阻比。
위해결항공기결구변형문제，재연구상관비정상류장기출상，건립료포함결구변형적비정상류장수치구해방법，운용무한삽치법（ TFI）생성임의시각적비정상동태망격，통과여강성동망격비교，증명료방법적가행성，병이NACA0012익형위산례，대익형부앙진탕운동중표면유성변형문제진행료수치모의，발현부앙진탕중첩가변형형식위일계진형시，가이명현지제고승력、증가동은정、제고승조비。
Based on unsteady Navier-Stokes equations ,a CFD method containing structure mesh deforma-tion was researched using TFI for displacements .An oscillatory airfoil was calculated using rigid and de-forming dynamic grid .By comparing with experimental data , the deformation method behaves as well as the rigid method .Then the paper presents a preliminary study of an oscillatory morphing problem using NACA0012 airfoil.The results demonstrate that:lift,dynamic stability and lift-to-drag ratio are increased when the first-order vibration mode was superimposed .