Flow Computation for Three-Dimensional Wing in Ground Effect Using Multi-Block Technique

Hirata, Nobuyuki; Kodama, Y.

doi:10.2534/jjasnaoe1968.1995.49

Cited by 15 publications

(2 citation statements)

References 4 publications

(1 reference statement)

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“…Staunfenbiel (1987) analyzed the stability of WIG craft, emphasizing dependency of their aerodynamic coefficients on height. One of the first attempts to use viscous solvers of computational fluid dynamics to model three-dimensional WIG was described by Hirata and Kodama (1995). A number of extensions of the extreme-ground-effect (EGE) potential-flow theory for ram wings, including lift-augmenting mechanisms, compressibility effects, and stability, are detailed in the book by Rozhdestvensky (2000).…”

Section: Introductionmentioning

confidence: 99%

Modeling of Roll-Heave-Pitch Motions of a Ram Wing Translating over Non-uniform Surface

Matveev

2019

J. Marine. Sci. Appl.

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Ground-effect vehicles flying close to water or ground often employ ram wings which generate aerodynamic lift primarily on their lower surfaces. The subject of this paper is the 3-DOF modeling of roll, heave, and pitch motions of such a wing in the presence of surface waves and other ground non-uniformities. The potential-flow extreme-ground-effect theory is applied for calculating unsteady pressure distribution under the wing which defines instantaneous lift force and moments. Dynamic simulations of a selected ram wing configuration are carried out in the presence of surface waves of various headings and wavelengths, as well as for transient flights over a ground obstacle. The largest amplitudes of the vehicle motions are observed in beam waves when the periods of the encounter are long. Nonlinear effects are more pronounced for pitch angles than for roll and heave. The present method can be adapted for modeling of air-supported lifting surfaces on fast marine vehicles. Article Highlights• Ram wings flying close to water or ground surfaces can produce high aerodynamic lift.• Unsteady forces on wings moving over surface waves are modeled with a potential-flow method.• Dynamics of a ground-effect vehicle is studied at different wave headings and amplitudes.

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Section: Introductionmentioning

confidence: 99%

Modeling of Roll-Heave-Pitch Motions of a Ram Wing Translating over Non-uniform Surface

Matveev

2019

J. Marine. Sci. Appl.

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“…They found that the lift and drag coefficients of airfoils with ground effect are strongly influenced by the shape of region between the lower surface of the airfoil and the ground. Hirata and Kodama [3] simulated three-dimensional WIG effect using multi-block technique, the flows with different ground heights are computed. Kornev and Matveev [4] developed a complex numerical model based on nonlinear vortex lattice method (NVLM) for hydro-aerodynamic simulation of a WIG vehicle, and most important and necessary features of the WIG aero-hydrodynamics were taken into account properly.…”

Section: Introductionmentioning

confidence: 99%

Unsteady flow structure of an airfoil in ground effect

Qian

Dai

2010

J. Shanghai Univ.(Engl. Ed.)

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Particle image velocimetry (PIV) experimental results of wake flow structure of a NACA0012 airfoil with small attack angle mounted above water surface are introduced. The experiment was carried out in a small-scale wind-wave tunnel. The diameter of wind-wave tunnel test section is 1.7 m (long) × 0.4 m (width) × 0.4 m (height). The flow fields around the airfoil were measured under four different conditions by varying the distance between the airfoil and the water surface. The attack angle of the airfoil was kept 10 • during the experiment. For each experimental condition, the time series of particle images was captured to calculate continuous evolution of the velocity fields. The velocity fields were ensemble averaged to get the statistic parameters such as mean velocity and vorticity. Typical instantaneous velocity fields for each case are introduced to show the basic flow structure of wind surface flow separation. The aerodynamic loads acting on the airfoil are analyzed qualitatively according to the mean vorticity distribution in the flow field based on the theory of vorticity aerodynamics. The results indicate that the flow structures and drag/lift force of the airfoil alter remarkably with the changing distance between the airfoil and water surface.

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Steady aerodynamic characteristics of a wing flying over a nonplanar ground surface Part I: Rail

2006

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Flow Computation for Three-Dimensional Wing in Ground Effect Using Multi-Block Technique

Cited by 15 publications

References 4 publications

Modeling of Roll-Heave-Pitch Motions of a Ram Wing Translating over Non-uniform Surface

Modeling of Roll-Heave-Pitch Motions of a Ram Wing Translating over Non-uniform Surface

Unsteady flow structure of an airfoil in ground effect

Steady aerodynamic characteristics of a wing flying over a nonplanar ground surface Part I: Rail

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