翼上螺旋桨构型耦合气动特性及翼型优化设计

doi:10.7527/S1000-6893.2018.22777

Abstract

Abstract: This paper studies the characteristics of the propeller-wing coupled flow field of the channel wing configuration. It also carries out an airfoil optimization with the aim to improve the lift efficiency at Short Takeoff and Landing (STOL) condition. By adopting the momentum source method and carrying out the real blade model CFD analysis of the propeller-wing interaction flow field, this paper first analyzes the feasibility of the momentum source method for the design. Then, to obtain a new airfoil with coupled aerodynamic features, an parameterized model with Free-Form Deformation (FFD) method is established to optimize the airfoil of the channel wing, and the changes of optimal airfoil parameters and the flow field are analyzed. In the end, the CFD analysis for three dimensional channel wing is carried out to compare and verify the two-dimensional airfoil optimization results. The results show that the Multiple Reference Frame (MRF) method cannot correctly analyze the flow field of over-the-wing propeller, while the momentum source method is more consistent with the unsteady sliding mesh method. The genetic algorithm optimization using the two-dimensional momentum source CFD method is effective. With the protection of the half-duct, the advantages of two-dimensional optimization airfoil have been effectively inherited in the three-dimensional configuration. The airfoil design for channel wing configuration should focus on the curvature variation of the wing surface. In this paper, the Coanda effect is enhanced by increasing the curvature of the airfoil near the propeller and maintaining the attached flow, which achieved aerodynamic lift-increase. The lift of the optimal channel wing increases by 22.51%, and the high pressure area is significantly reduced behind the propeller and second peaks of suction appears, while drag is still negative.

Key words: propellers, wings, airfoils, vertical/short takeoff and landing, aerodynamics, channel wing

CLC Number:

V211

FAN Zhongyun, ZHOU Zhou, ZHU Xiaoping, GUO Jiahao. Coupled aerodynamic analysis and airfoil optimization design for over-wing propeller configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 122777-122777.

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[18]	HILL G A, KANDIL O A, HAHN A S. Aerodynamic investigations of an advanced over-the-wing nacelle transport aircraft configuration[J]. Journal of Aircraft, 2009, 46(1):25-35.
[19]	RAJAGOPALAN R G, LIM C K. Laminar flow analysis of a rotor in hover[J]. Journal of the American Helicopter Society, 1991, 36(1):12-23.
[20]	CHAFFIN M S, BERRY J D. Navier-Stokes simulation of a rotor using a distributed pressure disk method[C]//Proceedings of 51st Annual Forum of American Helicopter Society, 1995.
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[28]	UHLIG D V, SELIG M S. Post stall propeller behavior at low reynolds numbers[C]//AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA:AIAA, 2008.
[29]	许和勇, 叶正寅. 涵道螺旋桨与孤立螺旋桨气动特性的数值模拟对比[J]. 航空动力学报, 2011, 26(12):2820-2825. XU H Y, YE Z Y. Numerical simulation and comparison of aerodynamic characteristics between ducted and isolated propellers[J]. Journal of Aerospace Power, 2011, 26(12):2820-2825(in Chinese).
[30]	苏运德, 叶正寅,许和勇. 桨尖间隙和双桨间距对涵道螺旋桨气动性能的影响[J]. 航空动力学报, 2014, 29(6):1468-1475. SU Y D, YE Z Y, XU H H. Influence of tip clearance and propeller separation space on aerodynamic performance of ducted propeller[J]. Journal of Aerospace Power, 2014, 29(6):1468-1475(in Chinese).
[31]	李晓华, 郭正,陈清阳. 涵道螺旋桨气动特性数值模拟[J]. 国防科技大学学报, 2015(4):31-35. LI X H, GUO Z, CHEN Q Y. Numerical simulation of ducted rotor's aerodynamic characteristics[J]. Journal of National University of Defense Technology, 2015(4):31-35(in Chinese).
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Coupled aerodynamic analysis and airfoil optimization design for over-wing propeller configuration

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