Article
Engineering, Aerospace
Weihong Kong, You Li
Summary: This paper investigates the dynamic stall of airfoil in the reverse flow region of the rotor and develops a dynamic pressure measurement system to analyze its aerodynamic characteristics. The study shows that the airfoil is more prone to stall in the reverse flow region under static conditions, and the stall is not affected by the Reynolds number. In the dynamic environment, the pitching oscillation in the reverse flow region is more sensitive to changes in airfoil parameters compared to normal flow, and there is a significant difference. Increasing the reduced frequency leads to a more significant increase in the dynamic stall angle of attack.
Article
Engineering, Marine
Qing Wang, Muyao Yu, Deshun Li, Rennian Li
Summary: This study investigates the dynamic stall of the S809 airfoil under a sand-wind environment, which has rarely been considered in previous studies. The simulations reveal that sand particles with a diameter of 10 μm decrease the maximum lift coefficient and drag coefficient by approximately 2.18% and 2.52% respectively compared to clear air. Moreover, a particle concentration of 62.6 g/m3 results in a 6.93% decrease in the maximum lift coefficient. The results also indicate that the decrease in lift and drag coefficients becomes more significant with higher particle concentrations, suggesting reduced efficiency of wind turbines in sand storm weather.
Article
Engineering, Aerospace
Jiaqi Liu, Rongqian Chen, Yancheng You, Zheyu Shi
Summary: This study numerically investigates the suppression of dynamic stall in a rotor airfoil using the Co-Flow Jet (CFJ) method. The results show that the improved CFJ, specifically the CFJ-sloping slot, is more effective in suppressing shock-induced dynamic stall and dynamic stall at high angles of attack.
CHINESE JOURNAL OF AERONAUTICS
(2022)
Article
Chemistry, Multidisciplinary
Liming Wu, Xiaomin Liu
Summary: This study investigates the use of a bionic wavy leading edge airfoil to counteract the dynamic stall-induced aerodynamic changes, finding that the application of a sinusoidal leading edge can significantly reduce the maximum drag coefficient while only slightly reducing the maximum lift coefficient. The research also shows that the dynamic hysteresis effect improves gradually with an increasing waviness ratio.
APPLIED SCIENCES-BASEL
(2021)
Article
Engineering, Aerospace
Vishal Raul, Leifur Leifsson
Summary: The dynamic stall phenomenon is characterized by the formation of a leading-edge vortex, which impacts the structural strength and life of a system. Aerodynamic shape optimization provides a cost-effective method to delay or mitigate these characteristics, but it requires time-consuming CFD simulations. A surrogate-based optimization technique is proposed in this work to reduce the computational cost of ASO for airfoil dynamic stall characteristics.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Jiaqi Liu, Rongqian Chen, Jinhua Lou, Yue Hu, Yancheng You
Summary: This study utilizes a surrogate model based on deep learning to optimize the aerodynamic shape of rotor airfoils with the aim of suppressing dynamic stall. By combining deep neural network (DNN) with multi-island genetic algorithm, the optimization time can be greatly reduced. The results demonstrate that the optimized airfoil has significantly improved dynamic stall characteristics and achieves better aerodynamic performance than the baseline airfoil.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Multidisciplinary Sciences
Galih Bangga, Surya Hutani, Henidya Heramarwan
Summary: Increasing airfoil thickness is found to be beneficial in suppressing dynamic stall effects and improving the performance of high solidity turbines, despite a slight reduction in thrust component. The strength and radius of the dynamic stall vortex decrease with increasing airfoil thickness, which strongly influences the pressure distributions during the dynamic stall process.
ADVANCED THEORY AND SIMULATIONS
(2021)
Article
Green & Sustainable Science & Technology
D. De Tavernier, C. Ferreira, A. Vire, B. LeBlanc, S. Bernardy
Summary: The study demonstrates that vortex generators (VGs) can delay or suppress dynamic stall process in unsteady flow conditions, with important factors being VG height and mounting position. Configurations with VGs show a larger loss in normal coefficient when VG effectiveness vanishes, but the flow reattaches quicker and the airfoil recovers easier from deep-stall conditions.
Article
Energy & Fuels
Deshun Li, Ting He, Qing Wang
Summary: This paper investigates the impact of particle parameters on the airfoil dynamic stall through numerical simulation. The study reveals that the addition of particles reduces the aerodynamic performance of the airfoil, especially at large angles of attack. Moreover, the larger the particle diameter, the larger the vortex volume near the airfoil's leading edge, and a significant amount of particles gather at the suction surface of the airfoil. Additionally, as the particle concentration increases, the separation point of the airfoil occurs earlier and the erosion rate of the airfoil increases.
Article
Engineering, Aerospace
Binbin Wei, Yongwei Gao, Dong Li
Summary: Experimental study was conducted on the physics of the dynamic stall vortex (DSV) on the NACA 0012 airfoil, providing insight into the characteristics of DSV and its impact on aerodynamic performance.
INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES
(2021)
Article
Energy & Fuels
Tien-Dung Vuong, Kwang-Yong Kim
Summary: This study investigated the effects of a dual-bleeding port recirculation channel on the aerodynamic performance of a single-stage transonic axial compressor and optimized its configuration to enhance operating stability. The addition of the bleeding channel increased its stabilizing effect compared to a single-bleeding channel. Optimization resulted in a 51.36% increase in stall margin with only slight reductions in peak adiabatic efficiency and maximum pressure ratio.
Article
Thermodynamics
Chengyong Zhu, Yingning Qiu, Tongguang Wang
Summary: This paper presents comparative analyses of dynamic stall among the 2D airfoil, 3D non-rotating blade and 3D rotating blade undergoing sinusoidal pitch oscillations, with a focus on the impact of rotational augmentation on dynamic stall. The study found that rotational augmentation can effectively delay the onset of dynamic stall, increase the maximum lift coefficient, and significantly reduce the aerodynamic hysteresis intensity.
Article
Engineering, Mechanical
Erfan Salimipour, Shima Yazdani, Mehdi Ghalambaz
Summary: The present study numerically analyzed the effect of a passive flow control method on the dynamic stall phenomenon of an airfoil. The results showed that the control blade could effectively prevent separation bubble burst and reduce stall effects.
JOURNAL OF THE BRAZILIAN SOCIETY OF MECHANICAL SCIENCES AND ENGINEERING
(2022)
Article
Computer Science, Interdisciplinary Applications
Haris Moazam Sheikh, Sangjoon Lee, Jinge Wang, Philip S. Marcus
Summary: Design-by-Morphing (DbM) is a new design methodology that creates a search space for topology optimization. Unlike traditional techniques, DbM does not impose geometric constraints or designer biases on the design space, allowing for a radical and expansive search with minimal design parameters.
JOURNAL OF COMPUTATIONAL DESIGN AND ENGINEERING
(2023)
Article
Engineering, Aerospace
You Wu, Yuting Dai, Chao Yang, Yating Hu, Guangjing Huang
Summary: This paper investigates the use of phase-shifted trailing-edge morphing to suppress the pitching oscillation of a NACA 0012 airfoil. By employing numerical simulations and dynamic meshing techniques, it is concluded that phase-offset trailing-edge motion can effectively reduce energy extraction and suppress oscillation.
Article
Engineering, Aerospace
Andre F. P. Ribeiro, Carlos Ferreira, Damiano Casalino
Summary: This study compares a filament-based free wake panel method to experimental and validated numerical data in order to simulate propeller slipstreams and their interaction with aircraft components. The results show that the free wake panel method is able to successfully capture the slipstream deformation and shearing, making it a useful tool for propeller-wing interaction in preliminary aircraft design.
AEROSPACE SCIENCE AND TECHNOLOGY
(2024)