中文摘要：

基于一套高效通用的多层运动嵌套网格技术,建立了适合悬停状态倾转旋翼机旋翼/机翼气动干扰特性分析的高效混合计算流体力学（CFD）方法.在倾转旋翼/机翼贴体网格区采用可压雷诺平均Navier-Stokes（RANS）方程作为主控方程,过渡/背景网格区选用Euler方程,湍流模型选用Spalart-Allmaras模型.时间推进上采用双时间推进格式进行非定常求解,并在方法中运用了SPMD（Single Program Multiple Data）模式的并行加速技术.在此基础上,首先分别采用UH-60A直升机旋翼及XV-15倾转旋翼机旋翼作为数值算例,验证了CFD方法的有效性.然后着重对倾转旋翼/机翼的非定常干扰流场及气动力分布特征进行了数值研究,模拟得到与实际情况相符的“喷泉效应”干扰现象.计算结果表明,干扰作用使得倾转旋翼相对于孤立旋翼拉力数值减小了3％,但总的拉力系数损失达到了17％,证明悬停状态下气动干扰对飞行器气动性能有重要影响.

英文摘要：

Based on the multi-layer moving-embedded grid technique,an efficient hybrid computational fluid dynamics （CFD） method is developed to analyze the aerodynamic interaction characteristics of the tiltrotor and wing in hover.A highly-efficient multi-layer moving-embedded grid technique is first established.Compressible Reynolds-averaged Navier-Stokes （RANS） equations with an Spalart-Allmaras turbulence model are employed in the tiltrotor/wing grid region,while Euler equations are chosen to simulate the transition/background region.In order to solve the unsteady flowfield of the tiltrotor/wing,a dual-time method is used.In the present study,the SMPD （Single Program Multiple Data） model parallel acceleration technology is adopted.On this basis,a UH-60A rotor and XV-15 tiltrotor are taken as numerical examples to verify the validity of the established method.Then the unsteady interaction flowfield of the tiltrotor/wing are investigated in detail,and the special ＂fountain effect＂ phenomenon is simulated.Due to the interaction effect,the thrust coefficient of the tiltrotor is slightly decreased by 3％ than that of an isolated rotor,but the total thrust coefficient loss is about 17％ as compared to the isolated rotor.It is demonstrated that the tiltrotor/wing interaction in hover has significant effect on the aerodynamic performance of the tiltrotor aircraft.