Turbulent Flow Calculations on the Ground Effect about an Airfoil

Kim, Yoon-Sik; Lee, Jae Eun; Shin, Myung-Soo; Kang, Kuk-Jin; Kwon, Jang Hyuk

doi:10.2514/6.2007-4179

Cited by 3 publications

(3 citation statements)

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“…Ground Effect (GE) is a term used to describe the phenomenon in which the airflow around an aircraft change when the aircraft is flying close to the ground. This change in airflow causes the direction of the air flow to become parallel to the ground, resulting in different aerodynamic characteristics than those observed in free flow conditions [1] . During take-off and landing, all fixed-wing aircraft will experience GE and high-lift configuration is often used to improve the lift at low speeds and increase the lift-drag ratio.…”

Section: Introductionmentioning

confidence: 95%

Numerical simulation of two-dimensional plain flap ground effect based on NACA4412 airfoil

Xiao,

Wang,

Sun

2024

J. Phys.: Conf. Ser.

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Based on the NACA4412 airfoil, by solving a two-dimensional unsteady Reynolds-averaged N-S equation and using the k-ωSST model, this paper analyzes the influence of near-ground altitude change on different configuration flow fields under moving ground conditions and explores the variation law of wing pressure coefficient at different near-ground altitudes. The results show that the attraction of the upper airfoil is weakened by the GE (ground effect), the pressure of the lower airfoil is increased, and the upper and lower airfoils influence the lift change of the airfoil. With the decrease of near-ground altitude, at a certain AOA (angle of attack), the greater the flap angle is, the faster the suction loss on the upper wing surface is and the slower the pressure increases on the lower wing surface, and the lower the near-ground altitude corresponding to the minimum lift coefficient is. With the decrease of near-ground altitude, at a certain flap angle, the greater the AOA is, the faster the suction loss on the upper wing surface is and the slower the pressure increases on the lower wing surface, and the lower the near-earth altitude corresponding to the minimum lift coefficient is.

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Section: Introductionmentioning

confidence: 95%

Numerical simulation of two-dimensional plain flap ground effect based on NACA4412 airfoil

Xiao,

Wang,

Sun

2024

J. Phys.: Conf. Ser.

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“…Recently, Kim, et al (2006) numerically investigated two dimensional turbulent flow simulations on the low Mach number -high Reynolds number flow about the NACA 4412 airfoil are carried out as the airfoil approaches a ground. It has turned out that angle of attack between 2 and 8 degrees is recommended for the airfoil to utilize the benefit of ground effect.…”

Section: Introductionmentioning

confidence: 99%

Mean flow characteristics of two-dimensional wings in ground effect

Jung¹,

Yoon²,

Hu³

et al. 2012

International Journal of Naval Architecture and Ocean Engineeri

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“…They solved 3D incomepressible Navier-Stokes equations using the turbulence closure model, and focused on the flow structure according to the configuration of the main and vertical wings by which the high lift-to-drag ratio changes. Kim et al (2006) numerically investigated 2D turbulent flow simulations on the low Mach number -high Reynolds number flow about the NACA 4412 airfoil are carried out as the airfoil approaches a ground. It has turned out that angle of attack between 2° and 8° is recommended for the airfoil to utilize the benefit of ground effect.…”

Section: Introductionmentioning

confidence: 99%

Endplate effect on aerodynamic characteristics of three-dimensional wings in close free surface proximity

Jung¹,

Kim²,

Yoon³

et al. 2012

International Journal of Naval Architecture and Ocean Engineeri

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We investigated the aerodynamic characteristics of a three-dimensional (3D) wing with an endplate in the vicinity of the free surface by solving incompressible Navier-Stokes equations with the turbulence closure model. The endplate causes a blockage effect on the flow, and an additional viscous effect especially near the endplate. These combined effects of the endplate significantly reduce the magnitudes of the velocities under the lower surface of the wing, thereby enhancing aerodynamic performance in terms of the force coefficients. The maximum lift-to-drag ratio of a wing with an endplate is increased 46% compared to that of wing without an endplate at the lowest clearance. The tip vortex of a wing-with-endplate (WWE) moved laterally to a greater extent than that of a wing-without-endplate (WOE).This causes a decrease in the induced drag, resulting in a reduction in the total drag.

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Turbulent Flow Calculations on the Ground Effect about an Airfoil

Cited by 3 publications

References 0 publications

Numerical simulation of two-dimensional plain flap ground effect based on NACA4412 airfoil

Numerical simulation of two-dimensional plain flap ground effect based on NACA4412 airfoil

Mean flow characteristics of two-dimensional wings in ground effect

Endplate effect on aerodynamic characteristics of three-dimensional wings in close free surface proximity

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