Turbulence investigation of the NASA common research model wing tip vortex
Апстракт
The paper presents high-speed stereo particle image velocimetry investigation of the NASA Common Research Model wing tip vortex. A three-percent scaled semi span model, without nacelle and pylon, was tested in the 32- by 48-inch In draft tunnel, at the Fluid Mechanics Laboratory at the NASA Ames Research Center. Turbulence investigation of the wing tip vortex is presented. Measurements of the wing-tip vortex were performed in a vertical cross-stream plane three tip-chords downstream of the wing tip trailing edge with a 2 kHz sampling rate. Experimental data are analyzed in the invariant anisotropy maps for three various angles of attack (0 degrees, 2 degrees, and 4 degrees) and the same speed generated in the tunnel (V-infinity = 50 m/s). This corresponds to a chord Reynolds number 2.68.10(5), where the chord length of 3" is considered the characteristic length. The region of interest was x = 220 mm and y = 90 mm. The 20 000 particle image velocimetry samples were acquired at each cond...ition. Velocity fields and turbulence statistics are given for all cases, as well as turbulence structure in the light of the invariant theory. Prediction of the wing tip vortices is still a challenge for the computational fluid dynamics codes due to significant pressure and velocity gradients.
Кључне речи:
vortex / turbulence / invariant maps / high-speed stereo particle image velocimetry / Common Research ModelИзвор:
Thermal Science, 2017, 21, S851-S862Издавач:
- Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
Финансирање / пројекти:
- NASA Revolutionary Computational Aerosciences (RCA) project
- Примена савремених мерних и прорачунских техника за изучавање струјних параметара вентилационих система на моделу енергетски изузетно ефикасног (пасивног) објекта (RS-MESTD-Technological Development (TD or TR)-35046)
DOI: 10.2298/TSCI161005328C
ISSN: 0354-9836; 2334-7163 (online ed.)
WoS: 000418781900026
Scopus: 2-s2.0-85041661257
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Čantrak, Đorđe AU - Heineck, James T. AU - Kushner, Laura K. AU - Janković, Novica PY - 2017 UR - https://machinery.mas.bg.ac.rs/handle/123456789/2586 AB - The paper presents high-speed stereo particle image velocimetry investigation of the NASA Common Research Model wing tip vortex. A three-percent scaled semi span model, without nacelle and pylon, was tested in the 32- by 48-inch In draft tunnel, at the Fluid Mechanics Laboratory at the NASA Ames Research Center. Turbulence investigation of the wing tip vortex is presented. Measurements of the wing-tip vortex were performed in a vertical cross-stream plane three tip-chords downstream of the wing tip trailing edge with a 2 kHz sampling rate. Experimental data are analyzed in the invariant anisotropy maps for three various angles of attack (0 degrees, 2 degrees, and 4 degrees) and the same speed generated in the tunnel (V-infinity = 50 m/s). This corresponds to a chord Reynolds number 2.68.10(5), where the chord length of 3" is considered the characteristic length. The region of interest was x = 220 mm and y = 90 mm. The 20 000 particle image velocimetry samples were acquired at each condition. Velocity fields and turbulence statistics are given for all cases, as well as turbulence structure in the light of the invariant theory. Prediction of the wing tip vortices is still a challenge for the computational fluid dynamics codes due to significant pressure and velocity gradients. PB - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd T2 - Thermal Science T1 - Turbulence investigation of the NASA common research model wing tip vortex EP - S862 SP - S851 VL - 21 DO - 10.2298/TSCI161005328C ER -
@article{ author = "Čantrak, Đorđe and Heineck, James T. and Kushner, Laura K. and Janković, Novica", year = "2017", abstract = "The paper presents high-speed stereo particle image velocimetry investigation of the NASA Common Research Model wing tip vortex. A three-percent scaled semi span model, without nacelle and pylon, was tested in the 32- by 48-inch In draft tunnel, at the Fluid Mechanics Laboratory at the NASA Ames Research Center. Turbulence investigation of the wing tip vortex is presented. Measurements of the wing-tip vortex were performed in a vertical cross-stream plane three tip-chords downstream of the wing tip trailing edge with a 2 kHz sampling rate. Experimental data are analyzed in the invariant anisotropy maps for three various angles of attack (0 degrees, 2 degrees, and 4 degrees) and the same speed generated in the tunnel (V-infinity = 50 m/s). This corresponds to a chord Reynolds number 2.68.10(5), where the chord length of 3" is considered the characteristic length. The region of interest was x = 220 mm and y = 90 mm. The 20 000 particle image velocimetry samples were acquired at each condition. Velocity fields and turbulence statistics are given for all cases, as well as turbulence structure in the light of the invariant theory. Prediction of the wing tip vortices is still a challenge for the computational fluid dynamics codes due to significant pressure and velocity gradients.", publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd", journal = "Thermal Science", title = "Turbulence investigation of the NASA common research model wing tip vortex", pages = "S862-S851", volume = "21", doi = "10.2298/TSCI161005328C" }
Čantrak, Đ., Heineck, J. T., Kushner, L. K.,& Janković, N.. (2017). Turbulence investigation of the NASA common research model wing tip vortex. in Thermal Science Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 21, S851-S862. https://doi.org/10.2298/TSCI161005328C
Čantrak Đ, Heineck JT, Kushner LK, Janković N. Turbulence investigation of the NASA common research model wing tip vortex. in Thermal Science. 2017;21:S851-S862. doi:10.2298/TSCI161005328C .
Čantrak, Đorđe, Heineck, James T., Kushner, Laura K., Janković, Novica, "Turbulence investigation of the NASA common research model wing tip vortex" in Thermal Science, 21 (2017):S851-S862, https://doi.org/10.2298/TSCI161005328C . .