Design and performance of thin, circular arc, wind-tunnel turning vanes

Johl, G.; Passmore, Martin A.; Render, P. M.

doi:10.1017/s0001924000001810

Cited by 3 publications

(1 citation statement)

References 2 publications

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“…All other dimensional parameters are based on a scaled design outlined by Rozell [82], which is a standardized design used by the American Society of Heating, Refrigeration, and Air-Conditioning Engineers (ASHRAE). The positive angle of incidence of 2°is implemented to help prevent separation along the suction side of the vane [80]. Figure 2.41 shows the designed turning vane profile.…”

Section: Exhaust Corner Transition and Flow Turning Vanesmentioning

confidence: 99%

The Design, Fabrication, and Commissioning of a High-Speed Aeroacoustic Wind Tunnel for Studies of Surface Pressure Fluctuations Beneath Turbulent Boundary Layers

Giardino¹

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The High-Speed Aeroacoustic Wind Tunnel (HSAWT) at Carleton University is a newly commissioned facility with the purpose of facilitating experimental studies of Turbulent Boundary Layer (TBL) induced surface pressure fluctuations. This research is intended for applications regarding aircraft noise generation from structures exposed to high-speed flow. This open-jet, blowdown facility is unique in Canada and one of a few aeroacoustic wind tunnels in the world capable of achieving speeds up to Mach 0.8. The details of the complete design and fabrication methodology for all wind tunnel duct components, control system hardware, and instrumentation systems is discussed; along with the numerical simulations performed in the validation of the designed components. Preliminary experimental flow measurements and characterization of the wind tunnel control system is examined. The results of initial measurements of TBL surface pressure fluctuations developed over a flat test section plate are compared with established data and empirical models in literature. iv Acknowledgements First and foremost, I would like to thank my thesis and research supervisor, Professor Joana Rocha, for her support and invaluable guidance provided throughout my entire Master's Degree program. Our countless free and open discussions during research meetings has helped me to develop a better understanding and appreciation regarding the complex topics of fluid mechanics and aeroacoustics. I have no doubt that my experiences the past couple of years as a part of her research team will benefit me in my future career initiatives and endeavors.

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Section: Exhaust Corner Transition and Flow Turning Vanesmentioning

confidence: 99%

The Design, Fabrication, and Commissioning of a High-Speed Aeroacoustic Wind Tunnel for Studies of Surface Pressure Fluctuations Beneath Turbulent Boundary Layers

Giardino¹

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Design and Characterization of a High-Speed Subsonic Aeroacoustic Wind Tunnel

Giardino

Rocha

2019

Journal of Aircraft

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Practical Design of a Low-Cost Icing Wind Tunnel for Unmanned Aerial Vehicle Testing in a Limited Space

Plaza del Pino,

Terroba Ramírez,

García-Magariño

et al. 2024

Applied Sciences

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Ice accretion on aircrafts due to atmospheric conditions is still a relevant research topic, especially in the case of Unmanned Aerial Vehicles (UAVs), due to their smaller size and the relative underdevelopment of ice protection systems (anti-icing and de-icing) for these aircraft. For the research and development of these systems, it is necessary to assess their performance in icing wind tunnels (IWTs), which are generally high-cost facilities. This article describes the design and building process of a new IWT for testing fixed-wing UAVs, aimed at cost reduction and restricted to an existing cold climate chamber of limited size. The designed IWT is an open-circuit type with two corners, a test section size of 0.40 m × 0.27 m and speed up to 70 m/s. The design process employs widely used and proven semi-empirical formulas, supported by detailed calculations using Computational Fluid Dynamics (CFD) tools, to achieve a test section core of useful quality and avoid flow separation. Theoretical limits with respect to a usable droplet size and Liquid Water Content (LWC) are calculated, and the test section core is estimated. The design process followed proves to be a very good approach to the design and aerodynamic optimisation of a low-cost IWT.

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Design and performance of thin, circular arc, wind-tunnel turning vanes

Cited by 3 publications

References 2 publications

The Design, Fabrication, and Commissioning of a High-Speed Aeroacoustic Wind Tunnel for Studies of Surface Pressure Fluctuations Beneath Turbulent Boundary Layers

The Design, Fabrication, and Commissioning of a High-Speed Aeroacoustic Wind Tunnel for Studies of Surface Pressure Fluctuations Beneath Turbulent Boundary Layers

Design and Characterization of a High-Speed Subsonic Aeroacoustic Wind Tunnel

Practical Design of a Low-Cost Icing Wind Tunnel for Unmanned Aerial Vehicle Testing in a Limited Space

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