Numerical method of estimating and optimizing supersonic aerodynamic characteristics of arbitrary planform wings

1965 ◽  
Vol 2 (4) ◽  
pp. 261-265 ◽  
Author(s):  
WlLBUR D. MlDDLETON ◽  
HARRY W. CARLSON
Keyword(s):  
Numerical Method ◽  
Aerodynamic Characteristics ◽  
Arbitrary Planform

scholarly journals Experiments and numerical calculation to determine aerodynamic characteristics of flows around 3D wings

2014 ◽  
Vol 36 (2) ◽  
pp. 133-143 ◽  
Author(s):  
Nguyen Hong Son ◽  
Hoang Thi Bich Ngoc ◽  
Dinh Van Phong ◽  
Nguyen Manh Hung
Keyword(s):  
Numerical Calculation ◽  
Wind Tunnel ◽  
Pressure Distribution ◽  
Numerical Method ◽  
Aerodynamic Characteristics ◽  
Numerical Results ◽  
Computational Method ◽  
Wing Surface ◽  
Thickness Profile

The report presents method and results of experiments in wind tunnel to determine aerodynamic characteristics of 3D wings by measuring pressure distribution on the wing surfaces. Simultaneously, a numerical method by using sources and doublets distributed on panel elements of wing surface also is carried out to calculate flows around 3D wings. This computational method allows solving inviscid problems for wings with thickness profile. The experimental and numerical results are compared to each other to verify the built program that permits to extend the range of applications with the variation of wing profiles, wing planforms, and incidence angles.

scholarly journals Numerical method for an assessment of steady and motion-excited flowfields in a transonic cascade wind tunnel

2017 ◽  
Vol 1 ◽  
pp. QL9XVI ◽  
Author(s):  
Atsushi Tateishi ◽  
Toshinori Watanabe ◽  
Takehiro Himeno ◽  
Seiji Uzawa
Keyword(s):  
Wind Tunnel ◽  
Flow Field ◽  
Numerical Method ◽  
Aerodynamic Characteristics ◽  
Pressure Amplitude ◽  
Tunnel Wall ◽  
Flow Simulations ◽  
Influence Coefficients ◽  
The Difference ◽  
Transonic Cascade

AbstractThis article presents a numerical method and its application for an assessment of the flow field inside a wind tunnel. A structured computational fluid dynamics (CFDs) solver with overset mesh technique is developed in order to simulate geometrically complex configurations. Applying the developed solver, a whole transonic cascade wind tunnel is modeled and simulated by a two-dimensional manner. The upstream and downstream periodicity of the cascade and the effect of the tunnel wall on the unsteady flow field are focused on. From the steady flow simulations, the existence of an optimum throttle position for the best periodicity for each tailboard angle is shown, which provides appropriate aerodynamic characteristics of ideal cascades in the wind tunnel environment. Unsteady simulations with blade oscillation is also conducted, and the difference in the influence coefficients between ideal and wind tunnel configurations becomes large when the pressure amplitude increases on the lower blades.

Aerodynamic characteristics of the wing’S compartment using a numerical method with viscosity

2014 ◽  
Vol 0 (10) ◽  
pp. 92-100
Author(s):  
Игорь В. Король ◽  
Александра Д. Молодчик
Keyword(s):  
Numerical Method ◽  
Aerodynamic Characteristics

scholarly journals Wake-induced oscillation behaviour of twin bundle conductor transmission lines

2018 ◽  
Vol 5 (6) ◽  
pp. 180011 ◽  
Author(s):  
Chuan Wu ◽  
Bo Yan ◽  
Guizao Huang ◽  
Bo Zhang ◽  
Zhongbin Lv ◽  
...  
Keyword(s):  
Numerical Method ◽  
Transmission Lines ◽  
Wind Tunnel Test ◽  
Simulation Method ◽  
Aerodynamic Characteristics ◽  
Control Technique ◽  
Wind Velocities ◽  
Conductor Line ◽  
Wake Zone ◽  
Lift And Drag

A numerical method to simulate air flow around a bundle conductor line by means of the FLUENT software is presented and verified by a wind tunnel test for aerodynamic characteristics of a twin bundle conductor line. The lift and drag coefficients of the leeward sub-conductor of a twin bundle conductor varying with its relative position in the wake zone to the windward one under different wind velocities are numerically determined by the presented method. A user-defined subroutine of ABAQUS software is developed to apply the aerodynamic loads on each sub-conductor and the electromagnetic force between sub-conductors. The numerical simulation method for wake-induced oscillation of a bundle conductor line is proposed. By means of the numerical method, wake-induced oscillation processes of twin bundle conductor transmission lines under different parameters, including current intensity, spacer layout, span length and wind velocity, are numerically simulated. Moreover, the effects of those parameters on the oscillation characteristics of the lines, such as vibration mode, frequency, amplitude and motion trace, are discussed. The results obtained provide a fundamental basis for the understanding of wake-induced oscillation behaviour of twin bundle conductor transmission lines and the development of control technique for wake-induced oscillation.

Validation of Numerical Analysis to Estimate Airfoil Aerodynamic Characteristics at Low Reynolds Number Region

2015 ◽  
Author(s):  
Donghwi Lee ◽  
Taku Nonomura ◽  
Akira Oyama ◽  
Kozo Fujii
Keyword(s):  
Reynolds Number ◽  
Numerical Method ◽  
Low Reynolds Number ◽  
Lift Coefficient ◽  
Three Dimensional ◽  
Aerodynamic Characteristics ◽  
Navier Stokes ◽  
Two Dimensional ◽  
Eddy Simulation ◽  
Low Reynolds

In this study, two-dimensional laminar simulation (2-D Lam), two-dimensional Reynolds Averaged Navier-Stokes simulation with the Spalart-Allmaras turbulence model (2-D RANS(SA)), and implicit three-dimensional large-eddy simulation (3-D LES) are performed for NACA0012, NACA0006, and Ishii airfoils at Rec = 3.0 × 104. The relation between a predictability of airfoil aerodynamic characteristics and a dependence of airfoil geometry shape of each numerical method is evaluated at the low Reynolds number. Although little discrepancy is observed for the lift coefficient predictability, significant differences are presented in terms of the separation and reattachment points predictability depending on the numerical methods. The 2-D Lam simulation can predict the lift coefficients as well as the separation and reattachment points qualitatively as similar to the 3-D LES results except for the high angle of attack which is accompanied by the massive separation. The 2-D RANS(SA), the weak nonlinearity and stall phenomena for the lift coefficients are observed. A good predictability of the separation point are shown, however, it cannot be estimated the reattachment points due to the trend to predict widely for the separation region. The predictabilities of each numerical method appear regardless of the airfoil shapes.

Aerodynamic Characteristics of an Airfoil with Boundary Layer Ingestion in Subsonic Flow

2014 ◽  
Vol 670-671 ◽  
pp. 609-612 ◽  
Author(s):  
Jiang Hao Wu ◽  
Xue Mei Li
Keyword(s):  
Boundary Layer ◽  
Numerical Method ◽  
Mass Flow ◽  
Small Angle ◽  
Subsonic Flow ◽  
Angle Of Attack ◽  
Aerodynamic Characteristics ◽  
Pitching Moment ◽  
Flow Ratio ◽  
Mass Flow Ratio

The influence of boundary layer ingestion (BLI) on the aerodynamics of airfoil RAE2822 in subsonic is investigated by numerical method. Based on the calculation, it is found that the mass flow ratio (MFR), intake height, cowl length and intake position in the chord can affect on the lift, drag and pitching moment remarkable. Considering a maximum lift-over-drag, intake position in the chord should be rearward as possible with a certain high MFR at a small angle of attack and a considerable intake height. There is a proper MFR which makes drag lowest.

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