A Computational Tool For Unsteady Aerodynamic Flow Simulations Coupled With Rigid Body Dynamics And Control

Camargo, Jonathan; López, Omar D.; Ochoa-Lleras, Nicolas

doi:10.2514/6.2012-3034

Cited by 6 publications

(4 citation statements)

References 7 publications

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“…By doing so, the mesh cells are stretched and compressed along the outer domain where the oscillation takes place. In addition to the long computational time associated with mesh deformation, this approach can cause a high level of skewness inside the domain which may lead to poor mesh quality [10], [11]. For the present study, the mesh quality of the computational domain is of primary importance and therefore the mesh morphing strategy was considered to not be suitable.…”

Section: Non-inertial Frame Of Referencementioning

confidence: 99%

“…A modified solver was compiled in OpenFOAM v2.3.x to add the acceleration term presented in (1). An additional boundary condition library was used to modify the Dirichlet boundary condition [11]. The fluctuating inflow velocity to represent rotor surge oscillation in the moving reference frame was modelled as a simple sinusoid:…”

Section: Non-inertial Frame Of Referencementioning

confidence: 99%

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effects of surge motion on floating horizontal axis tidal turbines

Osman¹,

Willden

Vogel³

2020

Int. J. Mar. Ene.

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Wave induced motions due to actual sea state conditions will impact the performance of floating horizontal axis tidal turbine systems. This paper presents the results from numerical simulations of a 3-bladed horizontal axis tidal turbine oscillating in surge motion in a moving reference frame. The optimum tip-speed ratio, λ = 4.4 and k-ω SST turbulence model were used in the present study. The Navier-Stokes equation was modified by adding an inertial term to the equation and the Dirichlet boundary condition was also modified in order to simulate in the moving reference frame. The surge oscillations were parameterised in terms of the ratio of surge amplitude to rotor radius, A*, and the ratio of oscillation frequency to the rotational frequency of the rotor, ω*. A series of tests were conducted to study the effect of each parameter on the hydrodynamic performance of the tidal turbine. The results show that stall can occur on the blade when the velocity relative to the rotor is sufficiently high. In certain cases, negative thrust and power coefficients were observed when the velocity relative to the rotor is low. The fluctuation in blade loading increases together with the amplitude and frequency of oscillation, which will contribute to the fatigue of the rotor.

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Section: Non-inertial Frame Of Referencementioning

confidence: 99%

Section: Non-inertial Frame Of Referencementioning

confidence: 99%

effects of surge motion on floating horizontal axis tidal turbines

Osman¹,

Willden

Vogel³

2020

Int. J. Mar. Ene.

View full text Add to dashboard Cite

show abstract

“…Examples include SPINNER [2], NSWCAP [3], MC-DRAG [4], MISSILE [5], AP98 [6], DATCOM [6]. In contrast, computational methods [7][8][9][10][11][12] using CFD packages provide more accuracy and flexibility for non-conventional shapes and better insight into the physics of drag. Experimental techniques include Drag is indirectly estimated from flight data.…”

Section: Introductionmentioning

confidence: 99%

Assessment of drag prediction techniques based on radar data for supersonic vehicles

Doso,

Khali,

Zakaria

et al. 2023

J. Phys.: Conf. Ser.

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Flight testing is probably the most accurate approach for defining the aerodynamic characteristics of a flying vehicle. This is justified by the fact that compared to other approaches, either engineering or computational ones, flight testing is indeed the one that perfectly resembles the real flight environment. Flight data are either obtained by measuring the vehicle’s kinematics via onboard sensors or by tracking the vehicle’s flight via (commonly) radars. The advantages of the latter approach are evident in cases where modifying the vehicle design is not possible or in cases where rival/enemy vehicles are examined. The key issue for this approach is the quality and demands of the technique by which vehicle aerodynamic characteristics are reduced from flight-tracked data. In the open literature, different techniques are used to analyze radar data of vehicle position and utilize them to predict vehicle drag coefficient. Each technique has its strengths and pitfalls. In this paper, the three well-used techniques of drag estimation from radar data namely, Least Square (LS), Maximum Likelihood Estimation (MLE), and Stepwise regression (SR), are considered. The underlying principle, the output, and the range of validity for each technique are addressed with emphasis on what differentiates each of them. The viability and validity of the three techniques are addressed based on the own flight testing of a free-flight supersonic vehicle and using the point-mass flight model. Meteorological data are also recorded and flight conditions are used to enhance the resulting calculations. Based on experimental data available from the literature, a comparison is conducted for the techniques examined. Considering the lack of flight data utilized, and in conjunction with data from the literature, it has been concluded that the SR technique outperforms for a higher sample rate, however, the MLE is more feasible when there is a lack of data.

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“…Schutte et al 8 designed coupled CFD/ RBD method to estimate stability and control characteristics of X-31 configuration. Camergo et al 9 proposed a coupled CFD/RBD methodology to predict the transient flow field of aircrafts.…”

Section: Introductionmentioning

confidence: 99%

Computational fluid dynamics-based virtual flight simulation of a flying wing micro air vehicle

Cai

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, a computational fluid dynamics-based computational method is developed to simulate the virtual flight of a flying wing micro air vehicle. The virtual flight simulation model is composed of unsteady Reynolds averaged Navier-Stokes equations, motion equations, and flight control equations. The flow solver is established based on low Mach number preconditioning method, momentum source method, implicit dual time-stepping algorithm, and lower upper symmetric Gauss-Seidel iteration scheme on hybrid dynamic meshes. S-A turbulence model is also introduced to close the Reynolds averaged Navier-Stokes equations. Fourth-order Adams prediction-correction method is adopted to couple computational fluid dynamics and rigid body dynamics. The multidisciplinary computational method is validated as a reliable tool for virtual flight simulation through simulating wing-rock motion of a delta wing. Finally, the developed method is used to simulate the virtual flight of the micro air vehicle. The effectiveness of the computational method is proved in the virtual flight simulation.

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A Computational Tool For Unsteady Aerodynamic Flow Simulations Coupled With Rigid Body Dynamics And Control

Cited by 6 publications

References 7 publications

effects of surge motion on floating horizontal axis tidal turbines

effects of surge motion on floating horizontal axis tidal turbines

Assessment of drag prediction techniques based on radar data for supersonic vehicles

Computational fluid dynamics-based virtual flight simulation of a flying wing micro air vehicle

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