Direct Numerical Simulations on the three-dimensional wake transition of flows over NACA0012 airfoil at Re = 1000

Kouser，Taiba1; Xiong，Yongliang1,2; Yang，Dan3; Peng，Sai4

2021-11-01

10.1177/17568293211055656

International Journal of Micro Air Vehicles   影响因子和分区

1756-8293

1756-8307

For micro air vehicles (MAV), the precise prediction of aerodynamic force plays an important role. The aerodynamic force of a comparative low Reynold number (Re) vehicle tends to be affected by the different flow modes. In this paper, the aerodynamic performance of a three-dimensional NACA0012 airfoil is studied numerically. A range of angles of attack (α) 0°−25° and Reynolds number 1000 is considered. Mean and fluctuating coefficients of aerodynamic forces around NACA0012 airfoil are analyzed for different wake modes. The difference of aerodynamic forces between two and three-dimensional simulations are compared. The results show that the wake remains steady two-dimensional for lower angles of attack. At α = 9°, Von Karman vortex pattern is noticed. Flow transition to three-dimensional as the angle of attack increases from α = 13°. 3D wake is found to be stable with parallel shedding mode for 14°-17°. However, these modes become finer with the gradual increase in angle of incidence. While, wake loses its three-dimensional stability to chaotic with gradual increment in angle of attack afterwards.

airfoil DNS transition vortex shedding wake modes

SCI ; EI

英语

其他

WOS:000724518700001

20214911259448

Airfoils ; Angle of attack ; Micro air vehicle (MAV) ; Reynolds number ; Vortex flow

Fluid Flow, General:631.1 ; Aerodynamics, General:651.1 ; Aircraft, General:652.1

2-s2.0-85120343562

Scopus

1.Department of Mechanics,School of Aerospace Engineering,Huazhong University of Science and Technology (HUST),Wuhan,China
2.Hubei Key Laboratory of Engineering Structural Analysis and Safety Assessment,Wuhan,China
3.School of Naval Architecture and Ocean Engineering,Huazhong University of Science and Technology (HUST),Wuhan,China
4.Shenzhen Key Laboratory of Complex Aerospace Flows,Department of Mechanics and Aerospace Engineering,Southern University of Science and Technology,Shenzhen,China

Kouser，Taiba,Xiong，Yongliang,Yang，Dan,et al. Direct Numerical Simulations on the three-dimensional wake transition of flows over NACA0012 airfoil at Re = 1000[J]. International Journal of Micro Air Vehicles,2021,13.

Kouser，Taiba,Xiong，Yongliang,Yang，Dan,&Peng，Sai.(2021).Direct Numerical Simulations on the three-dimensional wake transition of flows over NACA0012 airfoil at Re = 1000.International Journal of Micro Air Vehicles,13.

Kouser，Taiba,et al."Direct Numerical Simulations on the three-dimensional wake transition of flows over NACA0012 airfoil at Re = 1000".International Journal of Micro Air Vehicles 13(2021).