Flow transition from laminar to turbulent is prerequisite to decide whereabouts to apply surface flow control techniques. This appears missing in a number of works in which the control effects were merely investigated...Flow transition from laminar to turbulent is prerequisite to decide whereabouts to apply surface flow control techniques. This appears missing in a number of works in which the control effects were merely investigated without getting insight into alteration of transition position. The aim of this study is to capture the correct position of transition over NACA0012 aerofoil at different angles of attack. Firstly, an implicit, time marching, high resolution total variation diminishing （TVD） scheme was developed to solve the governing Navier-Stokes equations for compressible fluid flows around aerofoil sections to obtain velocity profiles around the aerofoil surfaces. Secondly, the linear instability solver based on the Orr-Sommerfeld equations and the eg methods were developed to calculate the onset of transition over the aerofoil surfaces. For the low subsonic Mach number of 0.16, the accuracy of the compressible solutions was assessed by some available experimental results of low speed incompressible flows. In all cases, transition positions were accurately predicted which shows applicability and superiority of the present work to be extended for higher Mach number compressible flows. Here, transition prediction methodology is described and the results of this analysis without active flow control or separation are presented.展开更多
The design principle and the structural characters of a new sine driving system apparatus, which have been used by NPU NF-3 wind tunnel in the dynamic stall experiments on the oscillating aerofoil model from 1994, is ...The design principle and the structural characters of a new sine driving system apparatus, which have been used by NPU NF-3 wind tunnel in the dynamic stall experiments on the oscillating aerofoil model from 1994, is introduced. Some measures to improve the stability and flexibility are studied. The obvious advantages of the system are its simple structure, convenient operation and more accurate sine relationship between the attack angle and the rotating angle of the aerofoil The driving system has been proved advisable comparing with the experimental results both abroad and in many dynamic tests in NF-3 wind tunnel. It can provide guidelines for the study of the aerodynamic properties on the oscillating aerofoil.展开更多
Momentum balances are used to derive the Kutta-Joukowsky equation for an infinite cascade of aerofoils and an isolated aerofoil. These derivations are simpler than those based on the Blasius theorem or more complex un...Momentum balances are used to derive the Kutta-Joukowsky equation for an infinite cascade of aerofoils and an isolated aerofoil. These derivations are simpler than those based on the Blasius theorem or more complex unsteady control volumes, and show the close relationship between a single aerofoil and an infinite cascade. The modification of lift due to the presence of another lifting body is similarly derived for a wing in ground effect, a biplane, and tandem aerofoils. The results are identical to those derived from the vector form of the Kutta-Joukowsky equation.展开更多
Commercially available wind-turbines are optimized to operate at certain wind velocity, known as rated wind velocity. For other values of wind velocity, it has different output which is lower than the rated output of ...Commercially available wind-turbines are optimized to operate at certain wind velocity, known as rated wind velocity. For other values of wind velocity, it has different output which is lower than the rated output of the wind plant. Wind mill can be designed to provide maximum power output at different wind velocities through modification of swept area to match with the wind speed available at the moment. This can result in higher power output at all the velocities except that at rated wind speed because of limitation of generator. This results in increased utilization of generation capacity of wind mill compared to its commercially designed counterpart. A theoretical simulation has been done to prove a new concept about swept area of wind turbine blade which results in a significant increase in the power output through the year. Simulation results of power extracted through normal wind blade design and new concept are studied and compared. The findings of the study are presented in graphical and tabular form. Study establishes that there can be a significant gain in the power output with the new concept.展开更多
Serrated leading edges are one of the most promising passive aerodynamic control methods for the reduction of aerofoil–turbulence interaction noise.To elucidate the possible physical mechanisms,the current paper stud...Serrated leading edges are one of the most promising passive aerodynamic control methods for the reduction of aerofoil–turbulence interaction noise.To elucidate the possible physical mechanisms,the current paper studies the simplified set-up with aerofoil–vortical gust interaction and proposes an analytical model by incorporating Fourier transform into the Wiener–Hopf method.The proposed model suggests that the serrations operate on the incident vortical gusts as convolution,which leads to the innovative concept that models serrations as transfer functions in the wavenumber domain.Overall,the current theoretical study could provide a unique insight of the inherent aerodynamic noise control mechanisms of leading-edge serrations.展开更多
Abstract The aerodynamic characteristics of elliptic airfoil are quite different from the case of con ventional airfoil for Reynolds number varying from about 104 to 106. In order to reveal the funda mental mechanism,...Abstract The aerodynamic characteristics of elliptic airfoil are quite different from the case of con ventional airfoil for Reynolds number varying from about 104 to 106. In order to reveal the funda mental mechanism, the unsteady flow around a stationary two-dimensional elliptic airfoil with 16% relative thickness has been simulated using unsteady Reynolds-averaged NavieStokes equations and the 7 Reot transition turbulence model at different angles of attack for flow Reynolds number of 5 x 10^5. The aerodynamic coefficients and the pressure distribution obtained by computation are in good agreement with experimental data, which indicates that the numerical method works well. Through this study, the mechanism of the unconventional aerodynamic characteristics of airfoil is analyzed and discussed based on the computational predictions coupled with the wind tunnel results. It is considered that the boundary layer transition at the leading edge and the unsteady flow separation vortices at the trailing edge are the causes of the case. Furthermore, a valuable insight into the physics of how the flow behavior affects the elliptic airfoil＇s aerodynamics is provided.展开更多
文摘Flow transition from laminar to turbulent is prerequisite to decide whereabouts to apply surface flow control techniques. This appears missing in a number of works in which the control effects were merely investigated without getting insight into alteration of transition position. The aim of this study is to capture the correct position of transition over NACA0012 aerofoil at different angles of attack. Firstly, an implicit, time marching, high resolution total variation diminishing （TVD） scheme was developed to solve the governing Navier-Stokes equations for compressible fluid flows around aerofoil sections to obtain velocity profiles around the aerofoil surfaces. Secondly, the linear instability solver based on the Orr-Sommerfeld equations and the eg methods were developed to calculate the onset of transition over the aerofoil surfaces. For the low subsonic Mach number of 0.16, the accuracy of the compressible solutions was assessed by some available experimental results of low speed incompressible flows. In all cases, transition positions were accurately predicted which shows applicability and superiority of the present work to be extended for higher Mach number compressible flows. Here, transition prediction methodology is described and the results of this analysis without active flow control or separation are presented.
文摘The design principle and the structural characters of a new sine driving system apparatus, which have been used by NPU NF-3 wind tunnel in the dynamic stall experiments on the oscillating aerofoil model from 1994, is introduced. Some measures to improve the stability and flexibility are studied. The obvious advantages of the system are its simple structure, convenient operation and more accurate sine relationship between the attack angle and the rotating angle of the aerofoil The driving system has been proved advisable comparing with the experimental results both abroad and in many dynamic tests in NF-3 wind tunnel. It can provide guidelines for the study of the aerodynamic properties on the oscillating aerofoil.
文摘Momentum balances are used to derive the Kutta-Joukowsky equation for an infinite cascade of aerofoils and an isolated aerofoil. These derivations are simpler than those based on the Blasius theorem or more complex unsteady control volumes, and show the close relationship between a single aerofoil and an infinite cascade. The modification of lift due to the presence of another lifting body is similarly derived for a wing in ground effect, a biplane, and tandem aerofoils. The results are identical to those derived from the vector form of the Kutta-Joukowsky equation.
文摘Commercially available wind-turbines are optimized to operate at certain wind velocity, known as rated wind velocity. For other values of wind velocity, it has different output which is lower than the rated output of the wind plant. Wind mill can be designed to provide maximum power output at different wind velocities through modification of swept area to match with the wind speed available at the moment. This can result in higher power output at all the velocities except that at rated wind speed because of limitation of generator. This results in increased utilization of generation capacity of wind mill compared to its commercially designed counterpart. A theoretical simulation has been done to prove a new concept about swept area of wind turbine blade which results in a significant increase in the power output through the year. Simulation results of power extracted through normal wind blade design and new concept are studied and compared. The findings of the study are presented in graphical and tabular form. Study establishes that there can be a significant gain in the power output with the new concept.
基金This work is partly supported by National Science Foundation of China(Grants 11772005,91852201)Ministry of Industry and Information Technology of China(Grant no.MJ-2015-F-012-03)the Research Grants Council of the Hong Kong Special Administrative Region(Grant no.16205317).
文摘Serrated leading edges are one of the most promising passive aerodynamic control methods for the reduction of aerofoil–turbulence interaction noise.To elucidate the possible physical mechanisms,the current paper studies the simplified set-up with aerofoil–vortical gust interaction and proposes an analytical model by incorporating Fourier transform into the Wiener–Hopf method.The proposed model suggests that the serrations operate on the incident vortical gusts as convolution,which leads to the innovative concept that models serrations as transfer functions in the wavenumber domain.Overall,the current theoretical study could provide a unique insight of the inherent aerodynamic noise control mechanisms of leading-edge serrations.
基金financially supported by National Natural Science Foundation of China(No.11372254)
文摘Abstract The aerodynamic characteristics of elliptic airfoil are quite different from the case of con ventional airfoil for Reynolds number varying from about 104 to 106. In order to reveal the funda mental mechanism, the unsteady flow around a stationary two-dimensional elliptic airfoil with 16% relative thickness has been simulated using unsteady Reynolds-averaged NavieStokes equations and the 7 Reot transition turbulence model at different angles of attack for flow Reynolds number of 5 x 10^5. The aerodynamic coefficients and the pressure distribution obtained by computation are in good agreement with experimental data, which indicates that the numerical method works well. Through this study, the mechanism of the unconventional aerodynamic characteristics of airfoil is analyzed and discussed based on the computational predictions coupled with the wind tunnel results. It is considered that the boundary layer transition at the leading edge and the unsteady flow separation vortices at the trailing edge are the causes of the case. Furthermore, a valuable insight into the physics of how the flow behavior affects the elliptic airfoil＇s aerodynamics is provided.
