A combined experimental and computational study of a vertical gust generator in a wind tunnel

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AIAA SciTech 2019 Paper Final.pdf (937.72 KB)

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https://arc.aiaa.org/doi/abs/10.2514/6.2019-2166

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https://doi.org/10.2514/6.2019-2166
 http://hdl.handle.net/11603/12765

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UMBC Mechanical Engineering Department
UMBC Faculty Collection
UMBC Student Collection

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Date

2019

Type of Work

conference papers and proceedings preprints
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Citation of Original Publication

Naresh Poudel, Meilin Yu, Zachary F. Smith, and John T. Hrynuk. "A combined experimental and computational study of a vertical gust generator in a wind tunnel", AIAA Scitech 2019 Forum, AIAA SciTech Forum, (AIAA 2019-2166) , https://doi.org/10.2514/6.2019-2166

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This work was written as part of one of the author's official duties as an Employee of the United States Government and is therefore a work of the United States Government. In accordance with 17 U.S.C. 105, no copyright protection is available for such works under U.S. Law.
Public Domain Mark 1.0

Subjects

vertical guest wind tunnel
Particle Image Velocimetry (PIV)
numerical simulations of low-Mach-number-preconditioned compressible Naiver-Stokes equations on unstructured grids using high-order spectral difference (SD)
gust response of Micro Air Vehicles (MAVs)

Abstract

Experimental and numerical studies have been performed to investigate the performance of a vertical gust generator in a wind tunnel. Results from both experimental Particle Image Velocimetry (PIV) and those from numerical simulations of low-Mach-numberpreconditioned compressible Naiver-Stokes equations on unstructured grids using high-order spectral difference (SD) agreed reasonably well with each other. The gust was generated by ducting flow through the floor of the wind tunnel and at the wall of the numerical domain. The gust velocity profile bends downstream when interacting with freestream causing the incoming freestream flow to bend upward. The vertical gust changed the effective angle of attack over the airfoil when interacting with the freestream velocity. Due to the interaction of gust over the airfoil, the stationary airfoil at a nominal zero degree angle of attack undergo flow separation under stalled conditions.