TY - GEN
T1 - The effect of freestream turbulence integral length scale on junction flow behavior
AU - Lange, Eric A.
AU - Lynch, Stephen P.
N1 - Funding Information:
This work was sponsored by the Office of Naval Research, ONR, under grant number N00014-15-1-2764; the views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Office of Naval Research, the U.S. Navy or the U.S. government. The authors would like to also acknowledge the assistance of Syed Elahi and Zachary Moul at Penn State University in constructing the test facility used in this work.
Publisher Copyright:
© 2020 American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Junction flow is a common feature in many flows of practical and natural importance. At the junction of a wall-mounted obstacle and the wall, significant unsteadiness exists due to the presence of the horseshoe vortex. This is a coherent vortex structure which forms in front of the leading edge of the obstacle and is wrapped around the obstacle by the incoming flow. In turbulent flow, the horseshoe vortex experiences highly unsteady and non-periodic large scale motions and breakdown events. This dynamic behavior contributes to significant dynamic pressure loading on the obstacle and augmented heat transfer on the local wall and leading edge surfaces. While recent studies of the horseshoe vortex have suggested that significant interaction may occur between freestream turbulence and the horseshoe vortex, the effect of freestream turbulence length scale on the behavior of the horseshoe vortex has not yet been systematically determined. This study investigates the effect of variation in streamwise integral turbulent length scale on the dynamics of the horseshoe vortex system in front of a symmetric wing for a range of Reynolds numbers, turbulence intensities, and integral length scales. Time-resolved stereo particle image velocimetry (SPIV) measurements show that for the range of parameters studied, unsteadiness in the junction is only affected by integral length scale under the conditions of low body thickness Reynolds number and large turbulence intensity. A vorticity tracking technique is used to show that this effect is due to the greater rate of impingement of large turbulence features at the wing leading edge with increased integral length scale under these conditions.
AB - Junction flow is a common feature in many flows of practical and natural importance. At the junction of a wall-mounted obstacle and the wall, significant unsteadiness exists due to the presence of the horseshoe vortex. This is a coherent vortex structure which forms in front of the leading edge of the obstacle and is wrapped around the obstacle by the incoming flow. In turbulent flow, the horseshoe vortex experiences highly unsteady and non-periodic large scale motions and breakdown events. This dynamic behavior contributes to significant dynamic pressure loading on the obstacle and augmented heat transfer on the local wall and leading edge surfaces. While recent studies of the horseshoe vortex have suggested that significant interaction may occur between freestream turbulence and the horseshoe vortex, the effect of freestream turbulence length scale on the behavior of the horseshoe vortex has not yet been systematically determined. This study investigates the effect of variation in streamwise integral turbulent length scale on the dynamics of the horseshoe vortex system in front of a symmetric wing for a range of Reynolds numbers, turbulence intensities, and integral length scales. Time-resolved stereo particle image velocimetry (SPIV) measurements show that for the range of parameters studied, unsteadiness in the junction is only affected by integral length scale under the conditions of low body thickness Reynolds number and large turbulence intensity. A vorticity tracking technique is used to show that this effect is due to the greater rate of impingement of large turbulence features at the wing leading edge with increased integral length scale under these conditions.
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U2 - 10.2514/6.2020-0095
DO - 10.2514/6.2020-0095
M3 - Conference contribution
AN - SCOPUS:85091780212
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
SP - 1
EP - 20
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -