ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Inverse Design Analysis Method on Rotor with Advanced Aerodynamic Configuration Based upon Target Pressure Distribution
Received date: 2013-04-18
Revised date: 2013-05-23
Online published: 2013-06-28
Supported by
National Natural Science Foundation of China (11272150)
An inverse design method for a helicopter rotor with advanced aerodynamic configuration is established based on Reynolds-averaged Navier-Stokes (RANS) equations, moving-embedded grids, target pressure distributions and the iterative residual correction principle. In order to avoid the distortion of the grids around the blade due to configuration change, a fast and automated generation method of the body-fitted and orthogonal grids around the rotor blade is employed by solving the Poisson equations. To improve the quality and robustness of the moving-embedded grids, a strategy of grid generation is proposed by combining the interpolation of section grids and the folding of blade tip grids. Simultaneously, a new approach for determining the hole boundary and searching donor cells is created by the combination of "Top Map" and "Inverse Map" methods. The solution of the unsteady flowfield of the rotor is accomplished by employing the Navier-Stokes equations and a dual-time scheme. The convective flux is calculated by a Roe-MUSCL scheme, and a preconditioning approach is employed to overcome the stiffness of flowfield convergence. Based upon the computational fluid dynamics (CFD) numerical simulation, the MGM (Modified Garabedia-McFadden) inverse design overdetermined equations are established at different azimuthal angles based on the residual of pressure coefficients, and the weight factors at different azimuthal angles are set up according to the restriction of shock wave separation and dynamic stall. An inverse design method for the aerodynamic configuration (airfoil) of the rotor is developed by the least square solution of the overdetermined MGM equations. The inverse design analyses on multi-target, multi-state and rotor (airfoil) aerodynamic configurations in forward flight are performed respectively by using the present method, and the effectiveness of the method is identified. Finally, the inverse design method is used successfully to design a rectangular rotor with new airfoils which possesses aerodynamic characteristics similar to the UH-60A helicopter rotor with its new tip blade.
ZHAO Guoqing , ZHAO Qijun . Inverse Design Analysis Method on Rotor with Advanced Aerodynamic Configuration Based upon Target Pressure Distribution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(3) : 744 -755 . DOI: 10.7527/S1000-6893.2013.0267
[1] Leishman J G. Rotorcraft aeromechanics: getting through the dip[J]. Journal of the American Helicopter Society, 2010, 55(1): 011001-1-011001-24.
[2] Wang S C, Xu G H. Progress of helicopter rotor aerodynamics[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2001, 33(3): 203-211. (in Chinese) 王适存, 徐国华. 直升机旋翼空气动力学的发展[J].南京航空航天大学学报, 2001, 33(3): 203-211.
[3] Yang H, Song W P, Han Z H, et al. Multi-objective and multi-constrained optimization design for a helicopter rotor airfoil[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(7): 1218-1226. (in Chinese) 杨慧, 宋文萍, 韩忠华, 等. 旋翼翼型多目标多约束气动优化设计[J]. 航空学报, 2012, 33(7): 1218-1226.
[4] Lee S W, Kwon O J. Aerodynamic shape optimization of rotor blades in hover using a unstructured meshes[C]//Proceedings of the 60th Annual Forum of AHS International, 2004, 1: 536-547.
[5] Wang B, Zhao Q J, Xu G H. Numerical optimization of helicopter rotor twist distribution in hover[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(7): 1163-1172. (in Chinese) 王博, 招启军, 徐国华. 悬停状态直升机桨叶扭转分布的优化数值计算[J].航空学报, 2012, 33(7): 1163-1172.
[6] Yu J, Paraschivoiu I, Saeed F. Iterative inverse design method based on streamline equations[J]. Journal of Aircraft, 2004, 41(4): 821-828.
[7] Liu X D, Yang X D. Inverse design for wing of multi-point aerodynamic based on adjoint method[J]. Aeronautical Computing Technique, 2012, 42(5): 60-64.(in Chinese) 刘晓冬, 杨旭东. 基于伴随方法的机翼多设计点气动反设计方法[J]. 航空计算技术, 2012, 42(5): 60-64.
[8] Garabedian P, Mcfadden G. Design of supercritical swept wings[J]. AIAA Journal, 1982, 20(3): 289-291.
[9] Kim H J, Rho O H. Aerodynamic design of transonic wings using the target pressure optimization approach[J]. Journal of Aircraft, 1998, 35(5): 671-677.
[10] Whyte P H. Use of CFD in helicopter aerodynamic design[J]. Canadian Aeronautics and Space Journal, 1988, 34(2): 92-101.
[11] Malone J B, Narramore J C. Airfoil design method using the N-S equations[J]. Journal of Aircraft, 1991, 28(3): 216-224.
[12] Hassan A A, Charles B D. Airfoil design for helicopter rotor blades-a three-dimensional approach[J]. Journal of Aircraft, 1997, 34(2): 197-205.
[13] Li J Z, Gao Z H, Zhan H. Study on inverse design method of airfoil based on optimization of target pressure distribution[J]. Journal of Projectiles Rockets Missiles and Guidance, 2008, 28(1): 187-190. (in Chinese) 李焦赞, 高正红, 詹浩. 基于目标压力分布优化的翼型反设计方法研究[J]. 弹箭与制导学报, 2008, 28(1): 187-190.
[14] Shang K M, Zhao Q J, Zhao G Q, et al. Inverse design analysis on helicopter rotor airfoils and aerodynamic shapes[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2010, 42(5): 550-556. (in Chinese) 尚克明, 招启军, 赵国庆, 等. 直升机旋翼翼型及桨叶气动外形反设计分析[J]. 南京航空航天大学学报, 2010, 42(5): 550-556.
[15] Tapia F, Sanker L N, Schrage D P. An inverse aerodynamic design method for rotor blades[J]. Journal of the American Helicopter Society, 1997, 42(4): 321-326.
[16] Hilgenstock A. A fast method for the elliptic generation of three-dimensional grids with full boundary control[C]//Proceedings of the Second International Conference, 1988: 137-146.
[17] Wang B, Zhao Q J, Xu G, et al. A new moving-embedded grid method for numerical simulation of unsteady flow-field of the helicopter rotor in forward flight[J]. Acta Aerodynamica Sinica, 2012, 30(1): 14-21. (in Chinese) 王博, 招启军, 徐广, 等. 一种适合于旋翼前飞非定常流场计算的新型运动嵌套网格方法[J]. 空气动力学学报, 2012, 30(1): 14-21.
[18] Zhao Q J, Xu G H, Zhao J G. Numerical simulations of the unsteady flowfield of helicopter rotors on moving embedded grids[J]. Aerospace Science and Technology, 2005, 9(2): 117-124.
[19] Pletcher R H, Chen K H. On solving the compressible Navier-Stokes equations for unsteady flows at very low mach numbers, AIAA-1993-3368[R]. Reston: AIAA, 1993.
[20] Breley W R, Mcdonald H. An overview and generalization of implicit Navier-Stokes algorithms and approximate factorization[J]. Computers & Fluids, 2001, 30(7-8): 807-828.
/
| 〈 |
|
〉 |
CJA