Experimental investigation of transverse and vortex gust encounters at low reynolds numbers

Hülya Biler, Girguis Sedky, Anya R. Jones, Murat Saritas, Oksan Cetiner

Araştırma sonucu: ???type-name???Makalebilirkişi

20 Atıf (Scopus)

Özet

This paper aims to study the lift response of transverse and vortex gust encounters. A sine-squared transverse gust was created in a water towing tank using a water jet, whereas a vortex gust was created in a water channel by clockwise half-rotation of an upstream gust generator plate. Forces and flowfields were acquired for both gust types. The effects of the gust ratio and vertical positioning of the gust generator plate were investigated for the transverse gust and the vortex gust encounters, respectively. For a flat plate at a 0 deg angle of attack, changing the gust ratio for the transverse gust was found to have a major effect on the peak lift and a minor effect on the recovery phase; whereas changing the vertical positioning of the gust generator plate for the vortex gust was found to cause relatively minor effects at almost every point in the lift response. Both gust encounters resulted in large transients in the lift force, and the unsteady forcing was found to depend on the circulation shed from the leading edge of the wing. The lift force experienced and the circulation shed showed a steeper increase for the transverse gust encounters despite the same gust ratio of one. Average velocity variations in time were obtained from the flowfield measurements along an upstream line for both gust types, and variations in the gust-induced angle of attack were computed. The Helmbold equation was then used to predict the lift coefficients based on the calculated gust-induced angle of attack. The trends in the measured and predicted lift coefficients were found to compare well with each other, but the values were found to agree well only when the gust-induced angle of attack was low.

Orijinal dilİngilizce
Sayfa (başlangıç-bitiş)786-799
Sayfa sayısı14
DergiAIAA Journal
Hacim59
Basın numarası3
DOI'lar
Yayın durumuYayınlandı - 2021

Bibliyografik not

Publisher Copyright:
© 2020 by The Authors.

Finansman

The work at the University of Maryland is supported in part by the U.S. Air Force Office of Scientific Research under grant FA9550-16-1-0508 and the National Science Foundation under grant no. 1553970. The work at Istanbul Technical University is supported by The Scientific and Technological Research Council of Turkey under grant no. 115M358, titled “For the Application on UAVs and MAVs, Gust Effect on the Performance of Wings in Motion (Maneuver or Flapping) and Flow Control Attempts.” The work at the University of Maryland is supported in part by the U.S. Air Force Office of ScientificResearch under grant FA9550-16-1-0508 and the National Science Foundation under grant no. 1553970.

FinansörlerFinansör numarası
U.S. Air Force Office of ScientificResearch
UAVs
National Science Foundation1553970
Air Force Office of Scientific ResearchFA9550-16-1-0508
Türkiye Bilimsel ve Teknolojik Araştirma Kurumu115M358
Istanbul Teknik Üniversitesi

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