湍流模型计算流体力学数值模拟翼型绕流松弛效应Numerical simulation of the flow around the NACA4412 airfoil is implemented based on Spalart-Allmaras (S-A), SST k-ω and Gao-Yong turbulence models.In our procedures,convection terms and diffusion terms are calculated using Roe scheme and center ...
Flying-hot-wire study of two-dimensional mean flow past an NACA4412 airfoil at maximum lift. AIAA, 1978:78—1196 8 Menter F R. Two-equation eddy-viscosity turbulence models for engineering applications.AIAA Journal, 1994; 32(8):1598—1605 9 Menter F, Rumsey C. Assessment of two-equation ...
The flow characteristics over a NACA4412 airfoil are studied in a low turbulence wind tunnel with moving ground simulation at a Reynolds number of 3.0 x 10... MR Ahmed,T Takasaki,Y Kohama - 《Aiaa Journal》 被引量: 110发表: 2012年 Flying-Hot-wire Study of Flow Past an NACA 4412 Airfoi...
THE EFFECTS OF REYNOLDS NUMBER, SECTION SHAPE, AND TURBULENCE STIMULATION ON THE LIFT OF A SERIES OF MODEL CONTROL SURFACES A series of model control surfaces with equal areas but varying aspect ratio was tested in a towing tank on a groundboard. The size of the fins, approximat... EM ...
Two low speed aerofoil design computer programs have been evaluated over a Reynolds number range of 2 × 105 to 1 × 106, using experimental data obtained from Cranfield’s 8′ × 6′ low speed wind tunnel, for a NACA 643–418...
.%对NACA4412翼型低速绕流进行了定常/非定常数值计算.对流项及扩散项的空间离散分别采用Roe格式和二阶中心格式,时间方向采用了二阶精度的双时间步隐式方法求解,湍流模式采用了两方程SST k-ω模式.将定常/非定常数值计算结果与实验数据进行了对比,非定常计算显示出了翼型尾缘附近周期性脱落涡现象,尾迹流动区里非...
In this article, the NACA 4412 profile, which has a wide usage area, high lift/drag ratio and a flat bottom surface, has been chosen as a wing concept for a hoverwing vehicle that operates by making use of ground effect. Turbulence modeling was carried out at flight al...
This Work Aims In Predicting The Flow Transition From Laminar To Turbulent For Flow Over NACA4412 Airfoil In The Incompressible Flow Regime.CFD Analysis Methodology Involves The Use Of Mentors Shear Stress Transport Turbulence Model(K-O Model)With Transitional Flow Option.CFD Analysis Results Are ...
A turbulent flow around a NACA4412 airfoil is simulated by a segregated finite element method based on the SIMPLE algorithmand the low Reynolds numberk-ω turbulence model. The originalk-ω model and a modified version of thek-ω, model (shear stress transport model) are adopted, for which ...
The computational method consists of a steady-state, incompressible, finite volume method utilizing the Spalart-Allmaras turbulence model. Grid generation and solution of the Navier-Stokes equations are completed flow with a flap, as well as ground-effect motion without a flap. Aerodynamic forces are...