CFD Simulation of a Wing-In-Ground-Effect UAV

Lao, Chung Ting

doi:10.1088/1757-899x/370/1/012006

Cited by 4 publications

(6 citation statements)

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“…The Spalart Allmaras model was chosen to analyze the turbulent behavior of the airflow around the tail-sitter. This model is commonly used in aerodynamic problems and is very suitable for predicting pressure gradients within the boundary layer [22]. The y + corresponding to this model is very low (y + < 5), which allows it to accurately predict aerodynamic properties close to the boundary layer compared to 2-equation models such as k − , whose y + is higher (y + < 30) [44][45][46].…”

Section: Determination Of Aerodynamic Coefficients By Means Of Cfd 22...mentioning

confidence: 99%

“…The geometric model for the numerical simulation as shown in Figure 11a is composed of two domains: the tail-sitter domain and the air enclosure domain. This model was carried out using the CAD ANSYS DesignModeler, in which, the domain of the tail-sitter was exported from the prototype built in CAD ANSYS SpaceClaim and the air enclosure domain was drawn based on [22,48]; the dimensions are described in Table 5. The computational domain shown in Figure 11b surrounded the tail-sitter aircraft, which has the same dimensions as the design stage.…”

Section: Geometric Modelmentioning

confidence: 99%

“…The rear wall was considered as the outlet boundary, with a gauge pressure outlet condition of 0 [Pa] (since the absolute pressure is equal to the atmospheric pressure). The other walls (upper, lower, right, and left sides) were considered as symmetry boundary conditions in a similar way to that of [22,48]. This allowed the air velocity to be maintained above zero in the area close to the walls to avoid the hydrodynamic boundary layer effect.…”

Section: Boundary Conditionsmentioning

confidence: 99%

“…The aerodynamic coefficients of drag and lift under different Mach numbers and different angles of attack were investigated numerically by means of CFD ANSYS Fluent software. Lao and Wong [22] carried out an aerodynamic study through CFD simulation that allowed for knowing the behavior of the aerodynamic properties (drag, lift, and moment coefficients) of an aircraft under different angles of attack. Combining the results from the lift and drag coefficients, it could be summarized that the lift-drag relationship is greatly improved by the ground effect.…”

Section: Introductionmentioning

confidence: 99%

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Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

et al. 2022

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Vertical take-off and landing (VTOL) aircraft have become important aerial vehicles for various sectors, such as security, health, and commercial sectors. These vehicles are capable of operating in different flight modes, allowing for the covering of most flight requirements in most environments. A tail-sitter aircraft is a type of VTOL vehicle that has the ability to take off and land vertically on it elevators (its tail) or on some rigid support element that extends behind the trailing edge. Most of the tail-sitter aircraft are designed with a fixed-wing adaptation rather than having their own design. The design of the tail-sitter carried out in this work had the particularity of not being an adaptation of a quad-rotor system in a commercial swept-wing aircraft, but, rather, was made from its own geometry in a twin-rotor configuration. The design was performed using ANSYS SpaceClaim CAD software, and a numerical analysis of the performance was carried out in ANSYS Fluent CFD software. The numerical results were satisfactorily validated with empirical correlations for the calculation of the polar curve, and the performance of the proposed tail-sitter was satisfactory compared to those found in the literature. The results of velocity and pressure contours were obtained for various angles of attack. The force and moment coefficients obtained showed trends similar to those reported in the literature.

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Section: Determination Of Aerodynamic Coefficients By Means Of Cfd 22...mentioning

confidence: 99%

Section: Geometric Modelmentioning

confidence: 99%

Section: Boundary Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

et al. 2022

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“…Deniz yüzeyi karasal bir yüzey ile kıyaslandığında daha stabil sınır değeri sağlamaktadır ve bu sebeple Wing-in-Ground-Effect taşıtlar yüksek hızlı deniz taşımacılığında kullanılması için daha uygun ve çevre dostudur. Belirtilen özellikleri dikkate alındığında uzun sahil şeridine sahip, ada veya adacıklardan ulaşan ülkeler için hızlı deniz taşımacılığı konusunda gelecek vadeden bir yere sahiptir [9].…”

Section: Gi̇ri̇ş (Introduction)unclassified

2D Investigation of a Wing Consept with a NACA 4412 Airfoil in Ground Effect Operation

Öztürk

Çinkir

Ürgün

et al. 2021

Gazi Üniversitesi Fen Bilimleri Dergisi Part C: Tasarım Ve Teknoloji

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In this study, Lift/Drag and Moment/Lift values of a wing concept with NACA 4412 airfoil under ground-effect conditions were investigated in 2D at varying altitudes. Figure A. Ground effect schematic and pressure distribution around airfoilPurpose: In this study, turbulence modeling of the wing concept designed for a hoverwing operating using ground effect has been made. At varying angles of attack and altitudes, altitude and angle of attack values were tried to be obtained where the maximum lift/drag and minimum moment/lift ratios were the most ideal.Theory and Methods: Analyzes were made using the ANSYS Fluent Academic program. It is made with a realizable k-ε turbulence model at 0 to 10 degrees of attack angles by decreasing by 0.1 chord in each step from 1 chord height to 0.1 chord height. In these analyzes, changes in lift/drag and moment/drag values were observed. Results:The values obtained after the analyzes were compared. It was observed that the maximum lift/drag ratio was obtained at an angle of attack of 4 degrees at an altitude corresponding to 0.1 chord height, and an increase of 38% compared to 1 chord height. Moment/drag, another factor that was taken into account when evaluating the analyzes, showed a remarkable decrease at 0 to 4 degrees of attack angle and changed very little after 4 angles of attack. Conclusion:It was observed that the NACA 4412 airfoil with a length of 2.75 m, which was analyzed, reached the values that it would be both the most efficient and balanced at 4 angles of attack under ground-effect conditions, but wind tunnel experiments were not carried out due to time and financial constraints. In order to make a definite judgment about the analysis results, wind tunnel experiments should definitely be done as a future study.

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Aerodynamics and flight performance of a UAV in ground effect based on flight simulation

Zhou

Mei

et al. 2023

AIAA SCITECH 2023 Forum

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CFD Simulation of a Wing-In-Ground-Effect UAV

Cited by 4 publications

References 1 publication

Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

Design and Determination of Aerodynamic Coefficients of a Tail-Sitter Aircraft by Means of CFD Numerical Simulation

2D Investigation of a Wing Consept with a NACA 4412 Airfoil in Ground Effect Operation

Aerodynamics and flight performance of a UAV in ground effect based on flight simulation

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