Flow Field around NACA0012 Airfoil at Low Reynolds Numbers

Ohtake, Tomohisa; Motohashi, Tatsuo

doi:10.2322/jjsass.57.397

Cited by 13 publications

(4 citation statements)

References 4 publications

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“…Note that the Ishii airfoil, which is the main wing airfoil of this airplane, has a low Reynolds number dependency on its lift curves at Re greater than 33,000 and at angles of attack that were below the stall angle (about 9°). 12 Therefore, we concluded that these differences in Reynolds number had little influence on the following discussion.…”

Section: Flight Historymentioning

confidence: 91%

Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Anyoji¹,

Okamoto²,

Fujita³

et al. 2017

FMRIJ

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In this study, we consider the development of a Mars airplane with a fixed wing, which is predicted to be a new Mars observation platform that will enable wide-range observation for Martian exploration. To validate our aerodynamic-design approach using wind tunnels and CFD analyses, we conduct a high-altitude flight test, termed Mars Airplane Balloon Experiment-1 (MABE-1), using Japan Aerospace Exploration Agency (JAXA)'s scientific ballooning (DAIKIKYU) and successfully obtain aerodynamic data for the airplane. This paper describes the results of aerodynamic characteristics from MABE-1 and provides a comparison with the wind tunnel test data.

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Section: Flight Historymentioning

confidence: 91%

Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Anyoji¹,

Okamoto²,

Fujita³

et al. 2017

FMRIJ

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“…The cycle-averaged effective angles of attack at 50% and 75% spans from the root were 28.7 and 15.8 degrees, respectively. In the stationary airfoil cases, the stall angle of the NACA0012 at Re c = 1.0 × 10 5 was approximately 11 degrees [29]. the azimuth angle  varies from 0 degree to 180 degrees.…”

Section: Flow Conditions and Wind Turbine Blade Modelmentioning

confidence: 95%

Separated Flow Control of Small Horizontal-Axis Wind Turbine Blades Using Dielectric Barrier Discharge Plasma Actuators

Aono

Fukumoto

et al. 2020

Energies

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The flow control over the blades of a small horizontal-axis wind turbine (HAWT) model using a dielectric barrier discharge plasma actuator (DBD-PA) was studied based on large-eddy simulations. The numerical simulations were performed with a high-resolution computational method, and the effects of the DBD-PA on the flow fields around the blades were modeled as a spatial body force distribution. The DBD-PA was installed at the leading edge of the blades, and its impacts on the flow fields and axial torque generation were discussed. The increase in the ratios of the computed, cycle-averaged axial torque reasonably agreed with that of the available experimental data. In addition, the computed results presented a maximum of 19% increase in the cycle-averaged axial torque generation by modulating the operating parameters of the DBD-PA because of the suppression of the leading edge separation when the blade’s effective angles of attack were relatively high. Thus, the suppression of the leading edge separation by flow control can lead to a delay in the breakdown of the tip vortex as a secondary effect.

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“…The streamlines around the wake of the foil are compared with the experimental result of Ohtake et al (2009). Due to the time is not clarified for the given streamline in the experiment, the present result is chosen at the instant the flow is stable.…”

Section: Wake Flow Around An Airfoil At Re = 10 000mentioning

confidence: 99%

“…In order to further verify the accuracy of the APR applied in the SPH method, the drag and lift coefficients acting on the airfoil in section 4.3 are compared with the experiment data of Ohtake et al (2009), and the results are shown in figures 17 and 18. It can be found that both the lift coefficient and drag coefficient regularly oscillate around the mean values of the experiment.…”

Section: Wake Flow Around An Airfoil At Re = 10 000mentioning

confidence: 99%

Improved adaptive particle refinement in δ-SPH and application to flow around bluff bodies simulation in different reynolds numbers

Yang¹,

Kang²,

Yan-min³

2020

Fluid Dyn. Res.

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Particle refinement technique uses spatially varying particle distributions that focus fine resolution on areas of interest to improve accuracy and computational efficiency of the smooth particle hydrodynamics (SPH) method, but its stability at coarse/fine interfaces can be problematic. Aiming at this problem, this paper improved adaptive particle refinement (APR) technology by optimizing the interpolation method of the particle parameters in buffer area and correcting the kernel gradient of particles troubled with boundary truncation to eliminate the truncation error. Based on the improved APR adopted in δ-SPH, the numerical simulation of the viscous flows around the bluff bodies under different Reynolds numbers were carried out. Additionally, the wake flows and hydrodynamic coefficients of the bluff bodies were systematically analyzed, respectively. The validity of the improved model was verified by comparing with the values in experiment and related literature, respectively. The calculated hydrodynamic coefficient achieves good agreement with the experimental data and the wake flow phenomena observed in experiment are clearly captured. The method adopted in this paper is effective and reliable, and has certain reference value for the research of fluid dynamics fields.

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Flow Field around NACA0012 Airfoil at Low Reynolds Numbers

Cited by 13 publications

References 4 publications

Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Separated Flow Control of Small Horizontal-Axis Wind Turbine Blades Using Dielectric Barrier Discharge Plasma Actuators

Improved adaptive particle refinement in δ-SPH and application to flow around bluff bodies simulation in different reynolds numbers

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