Experimental investigation of wing-in-ground effect with a NACA6409 section

Jung, Kwang Hyo; Chun, Ho Hwan; Kim, Hee Jung

doi:10.1007/s00773-008-0015-4

Cited by 51 publications

(27 citation statements)

References 5 publications

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“…An experimental simulation of WIG with NACA 6409 section based on ground clearance, angle of attack , aspect ratio and endplate type have been studied by Jun et al [4]. Ahmed and Sharma [3] studied experiment of pressure distribution through the wing surface with different ground clearances and angle of attack.…”

Section: Introductionmentioning

confidence: 99%

A CFD Study on Aerodynamic Characteristics of a Middle Wing for WIG Catamaran During Ground Effect

Priyanto¹,

Maimun²,

Jamei³

et al. 2010

AIP Conference Proceedings

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In this paper the influence of ground effect on the aerodynamic character of NACA 6409 were numerically studied. The simulations of the wing were performed by three dimensional Computational Fluid Dynamic (CFD). The important aerodynamic characters such as lift and drag coefficient, lift to drag ratio were determined with variation in some principle aerodynamic parameter, for instance the angle of attack and aspect ratio. The ground clearance ( h/c ) in CFD simulation was 0.1 . This simulation showed that there was enhancement on lift coefficient and reduction on drag coefficient related to incremental of aspect ratio when a aircraft flying in proximity to the ground. The K-ε turbulent model was used in CFD model. Numerical results were compared with experimental data of another researcher. As a application of this CFD simulation was calculating the lift-drag coefficient and lift to drag ratio from middle wing of WIG Catamaran.

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Section: Introductionmentioning

confidence: 99%

A CFD Study on Aerodynamic Characteristics of a Middle Wing for WIG Catamaran During Ground Effect

Priyanto¹,

Maimun²,

Jamei³

et al. 2010

AIP Conference Proceedings

View full text Add to dashboard Cite

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“…Due to the air cushion at low heights, there is a considerable increase in lift with a decrease in drag, and therefore enhancement of the lift-drag ratio [1][2][3][4][5]. The enhancement of the liftdrag ratio makes the WIG effect vehicle a potential means of transportation.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional flow characteristics of propeller-propulsion WIG effect vehicle with direct underside pressurization

Kim

Park

2011

J Mech Sci Technol

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Numerical investigations for a 3-dimensional WIG effect vehicle with DUP (direct underside pressurization) have been performed. The purpose of this study is to analyze the aerodynamic characteristics and static height stability of DUP using computational fluid dynamics (CFD). When a WIG effect vehicle accelerates to take off on water, increased pressure under the fuselage by DUP (propeller and air chamber) can considerably reduce the take-off speed and thus minimize the effect of the hump drag which is one of the technical difficulties of a WIG effect vehicle. The accelerated air by the propeller enters the air chamber through a channel in the middle of the fuselage resulting in an augmentation of the lift by changing the air pressure from dynamic to static. However, the DUP is not favorable for both stability and aerodynamic performance of the WIG effect vehicle because the accelerated air produces an excessive drag, negative pitching moment and 3-dimensional effects (that is, yawing and rolling moments). The result shows that the effect of yawing and rolling moments is not serious.

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“…7) Moon et al 8) simulated a three-dimensional (3D) WIG effect for an aero-levitation electric vehicle. Jung et al 9) tested the aerodynamic characteristics of NACA6409 in the ground proximity. Angle et al 10) focused their research on pitch stability analysis of an airfoil in the ground effect.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Investigation of Smart Flap Aerodynamics for a WIG Vehicle

Djavareshkian

Esmaeli

Parsania

et al. 2011

AEROSPACE TECHNOLOGY JAPAN

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Aerodynamic characteristics of a wing with a smart flap under the ground effect are studied through the integration of computational fluid dynamics. A parametric bending profile of a smart flap is designed considering different types of beams. Here, a cantilever beam with uniformly varying load with roller support at the free end is considered. The shape of the smart flap is fixed and its advantage comes from its smooth connection to the main wing. In this research, a pressure-based implicit procedure is used to solve Navier-Stokes equations. A non-orthogonal mesh with collocated finite volume formulation is utilized to simulate flow around the wing under the ground effect. First, the method is validated against experimental data. Then, the algorithm is applied for turbulent aerodynamic flows around a wing with smart and conventional flaps for different flap angles and ground clearance. The results of the two wings are compared. It is found that the pressure coefficient distribution for a wing with smart flaps is smoother than that of a wing with conventional flaps, and tip vortexes of the flap and wing diminish for low ground clearance. Finally, the maximum lift-to-drag ratio (L/D) is obtained for a smart wing when the angle of flap (AOF)=7.5˚ and h/c=0.3.

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Experimental investigation of wing-in-ground effect with a NACA6409 section

Cited by 51 publications

References 5 publications

A CFD Study on Aerodynamic Characteristics of a Middle Wing for WIG Catamaran During Ground Effect

A CFD Study on Aerodynamic Characteristics of a Middle Wing for WIG Catamaran During Ground Effect

Three-dimensional flow characteristics of propeller-propulsion WIG effect vehicle with direct underside pressurization

Three-Dimensional Investigation of Smart Flap Aerodynamics for a WIG Vehicle

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