Numerical bifurcation analysis of static stall of airfoil and dynamic stall under unsteady perturbation

Yan, Liang; Li, Kailun; Zhang, Jiazhong; Wang, Hang; Liu, Liguang

doi:10.1016/j.cnsns.2011.12.007

Cited by 59 publications

(37 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The unsteady vortex shedding phenomenon is observed at about α = 8 • , as for α < 8 • the numerical solution converges to steady state. This evidence is in agreement with results available in literature [43,44,45,46]. A further increasing of the angle of attack gives rise to leading-edge vortexes and flow instabilities at the rear of the airfoil become larger.…”

Section: Effect Of the Angle Of Attacksupporting

confidence: 93%

Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method

et al. 2018

View full text Add to dashboard Cite

We simulate the two-dimensional fluid flow around National Advisory Committee for Aeronautics (NACA) 0012 airfoil using a hybrid lattice Boltzmann method (HLBM), which combines the standard lattice Boltzmann method with an unstructured finite-volume formulation. The aim of the study is to assess the numerical performances and the robustness of the computational method. To this purpose, after providing a convergence study to estimate the overall accuracy of the method, we analyze the numerical solution for different values of the angle of attack at a Reynolds number equal to 10 3 . Subsequently, flow fields at Reynolds numbers up to 10 4 are computed for a zero angle of attack configuration. A grid refinement scheme is applied to the uniformly spaced component of the overlapping grid system to further enhance the numerical efficiency of the model. The results demonstrate the capability of the HLBM to achieve high accuracy near solid curved walls, thus providing a viable alternative in the realm of off-lattice Boltzmann methods based on body-fitted mesh.

show abstract

Section: Effect Of the Angle Of Attacksupporting

confidence: 93%

Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method

et al. 2018

View full text Add to dashboard Cite

show abstract

“…The result by Craig, et al [21] who conducted their experiment at a low Reynolds number (3.1x10 5 ) also shows a low slope of lift coefficient variation. The Reynolds number applied in this study is 10 5 which is higher than Re=10 3 of Liu, et al [19]. The fact, that the slope of lift coefficient variation becomes low due to the effect of the Reynolds number, can also be confirmed with the results by Hoerner & Borst [22].…”

Section: Resultssupporting

confidence: 87%

“…Though the lift coefficients differ from each other, the angle of attack where dynamic stall occurs is very similar. The calculated results were compared to the numerical results by Liu, et al [19] and the experimental results by Critzos, et al [20] who measured the lift and the drag coefficients at the angles of attack from 0° to 180°. The slope of lift coefficient variation of present calculation is lower than the experimental data at the region of low angle of attack.…”

Section: Resultsmentioning

confidence: 99%

Numerical Analysis of the Unsteady Subsonic Flow around a Plunging Airfoil

Lee¹,

Kim²

2013

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

Much numerical and experimental research has been done for the flow around an oscillating airfoil. The main research topics are vortex shedding, dynamic stall phenomenon, MAV's lift and thrust generation. Until now, researches mainly have been concentrated on analyzing the wake flow for the variation of frequency and amplitude at a low angle of attack. In this study, wake structures and acoustic wave propagation characteristics were studied for a plunging airfoil at high angle of attack. The governing equations are the Navier-Stokes equation with LES turbulence model. OHOC (Optimized High-Order Compact) scheme and 4th order Runge-Kutta method were used. The Mach number is 0.3, the Reynolds number is , and the angle of attack is from 20° to 50°. The plunging frequency and the amplitude are from 0.05 to 0.15, and from 0.1 to 0.2, respectively. Due to the high resolution numerical method, wake vortex shedding and pressure wave propagation process, as well as the propagation characteristics of acoustic waves can be simulated. The results of frequency analysis show that the flow has the mixed characteristics of the forced plunging frequency and the vortex shedding frequency at high angle of attack.

show abstract

“…Because of the complexity and nonlinear characteristics of the flow field in the rotating stall, such as aperiodicity, discontinuity and transition, a new method is developed to study the complex flow field of static and dynamic stalls on the basis of theory of nonlinear dynamics, especially the chaos and fractal theories [11,12]. The rotating stall in the centrifugal compressor in the general case is analyzed by an observation variable of the system which is a time series considered as a dynamic system, but the dynamic characteristics which are hidden in system cannot be shown directly by studying the time series of such state variables.…”

Section: Introductionmentioning

confidence: 99%

Identify the Rotating Stall in Centrifugal Compressors by Fractal Dimension in Reconstructed Phase Space

Wang

Zhang

2015

Entropy

Self Cite

View full text Add to dashboard Cite

Based on phase space reconstruction and fractal dynamics in nonlinear dynamics, a method is proposed to extract and analyze the dynamics of the rotating stall in the impeller of centrifugal compressor, and some numerical examples are given to verify the results as well. First, the rotating stall of an existing low speed centrifugal compressor (LSCC) is numerically simulated, and the time series of pressure in the rotating stall is obtained at various locations near the impeller outlet. Then, the phase space reconstruction is applied to these pressure time series, and a low-dimensional dynamical system, which the dynamics properties are included in, is reconstructed. In phase space reconstruction, C-C method is used to obtain the key parameters, such as time delay and the embedding dimension of the reconstructed phase space. Further, the fractal characteristics of the rotating stall are analyzed in detail, and the fractal dimensions are given for some examples to measure the complexity of the flow in the post-rotating stall. The results show that the fractal structures could reveal the intrinsic dynamics of the rotating stall flow and could be considered as a characteristic to identify the rotating stall.

show abstract

Numerical bifurcation analysis of static stall of airfoil and dynamic stall under unsteady perturbation

Cited by 59 publications

References 16 publications

Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method

Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method

Numerical Analysis of the Unsteady Subsonic Flow around a Plunging Airfoil

Identify the Rotating Stall in Centrifugal Compressors by Fractal Dimension in Reconstructed Phase Space

Contact Info

Product

Resources

About