流体力学与飞行力学

悬停状态倾转旋翼/机翼干扰流场及气动力的CFD计算

  • 李鹏 ,
  • 招启军
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  • 南京航空航天大学 直升机旋翼动力学国家级重点实验室, 江苏 南京 210016
李鹏 男,博士研究生。主要研究方向:旋翼计算流体力学、并行计算流体力学。Tel:025-84893753 E-mail:lp1987@nuaa.edu.cn;招启军 男,博士,教授,博士生导师。主要研究方向:直升机计算流体力学、直升机空气动力学及流动控制、气动噪声、总体设计。Tel:025-84893753 E-mail:zhaoqijun@nuaa.edu.cn

收稿日期: 2013-03-15

  修回日期: 2013-04-18

  网络出版日期: 2013-05-17

基金资助

国家自然科学基金(11272150)

CFD Calculations on the Interaction Flowfield and Aerodynamic Force of Tiltrotor/Wing in Hover

  • LI Peng ,
  • ZHAO Qijun
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  • Science and Technology on Rotorcraft Aeromechanics Laboratory, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2013-03-15

  Revised date: 2013-04-18

  Online published: 2013-05-17

Supported by

National Natural Science Foundation of China (11272150)

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。

本文引用格式

李鹏 , 招启军 . 悬停状态倾转旋翼/机翼干扰流场及气动力的CFD计算[J]. 航空学报, 2014 , 35(2) : 361 -371 . DOI: 10.7527/S1000-6893.2013.0220

Abstract

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 perfor-mance of the tiltrotor aircraft.

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