Journal ArticleDOI
Ground boundary layers effect on aerodynamic coefficients of a compound wing with respect to design parameters
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In this article, the effect of ground boundary layers on the aerodynamics of a compound wing of a wing-in-ground effect (WIG) craft was numerically investigated and the results were predicted to be able to provide a more fine-grained understanding on the ground viscous effect on WIG craft.About:
This article is published in Ocean Engineering.The article was published on 2018-09-15. It has received 6 citations till now. The article focuses on the topics: Lift-to-drag ratio & Drag coefficient.read more
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Journal ArticleDOI
Wake behind a Compound Wing in Ground Effect
Saeed Jamei,Adi Maimun,Rasul Niazmand Bilandi,Nor Azwadi,Simone Mancini,Luigi Vitiello,Maria De Carlini +6 more
TL;DR: In this paper, the authors investigated the pressure distribution around a compound wing, velocity and turbulent intensity distribution in the wake area after trailing of the wing, have been investigated numerically, and numerical results of the compound wing were validated using the data provided by wind tunnel tests.
Journal ArticleDOI
Vortical flow characteristics of a slender delta wing in ground effect
TL;DR: In this paper , the ground effect on the vortical flow structures over a 70-deg-swept slender delta wing qualitatively and quantitatively using dye flow visualization and Particle Image Velocimetry techniques were conducted in the plan-view, sideview and end-view planes with the angles of attack of α = 25° and 35°.
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A development of longitudinal static stability analysis method of a Wing-In-Ground effect vehicle in cruise during the design process
TL;DR: In this paper, the problem of development of WIG vehicle longitudinal static stability analysis method accounting the nonlinearity of pitch moment coefficient on lift force coefficient dependence for constant angle of attack is researched.
Journal ArticleDOI
Comparison of Economic and Transport Capabilities of Heavy C-type Airfield-Based WIG [Wing-in-Ground-Effect] Craft Versus Passenger Aircraft
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Short-takeoff marine vehicle with circulation flow control of wing-in-ground effect
TL;DR: In this article , the aerodynamic performance of a NACA 4412 airfoil that was modified for circulation control to determine the influence of the trailing-edge geometry, blowing coefficient, angle of attack, and height above the ground to improve the efficiency of a wing-in-ground craft and shorten its take-off distance.
References
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Journal ArticleDOI
Wing-in-ground effect vehicles
TL;DR: In this article, a survey of the research and development of wing-in-ground effect technology is presented, starting with definitions of the phenomenon and the craft which takes advantage of the ground effect (GE), the history and perspectives of the technology, specific vehicles and projects, and areas of application.
Journal ArticleDOI
An investigation on the aerodynamics of a symmetrical airfoil in ground effect
Mohammed R. Ahmed,S. D. Sharma +1 more
TL;DR: In this paper, the flow characteristics over a symmetrical airfoil were studied experimentally in a low speed wind tunnel, and the authors found that high values of pressure coefficient are obtained on the lower surface when the air foil is close to the ground.
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Aerodynamics of a NACA4412 airfoil in ground effect
TL;DR: In this paper, the flow characteristics over a NACA4412 airfoil were studied in a low turbulence wind tunnel with moving ground simulation at a Reynolds number of 3.0 x 105 by varying the angle of attack from 0 to 10 deg and ground clearance of the trailing edge from 5% of chord to 100%.
Wing in Ground Effect Craft Review
Michael Holloran,Sean O'Meara +1 more
TL;DR: In this paper, the authors present a design review of Wing in Ground Effect Craft (WIGs) and highlight the research required to overcome the weaknesses of WIG craft, the advantages that they may offer and the possible uses of the WIGs in the Australian military.
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Ground effect on flow past a wing with a NACA0015 cross-section
TL;DR: In this paper, a wind tunnel experiment was conducted on a wing with a NACA0015 cross-section, a chord of 0.24m and an aspect ratio of 1.46.