TY - GEN
T1 - Numerical simulation of wing section near stall
AU - Gross, A.
AU - Little, J.
AU - Fasel, H.
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - For the near-stall and fully stalled regime, where separation control is of interest, a limited amount of wing movement is always present. This is especially the case for high aspect ratio wings that exhibit some degree of structural flexibility such as seen on the X-56A. For the airfoil of the X-56A, wing section simulations were carried out for chord-based Reynolds numbers of Re=100,000 and 200,000. Below static stall (α≤12deg) a laminar separation bubble forms that gradually moves upstream towards the leading edge as the angle of attack is increased. When the wing section is subjected to high frequency plunging motions (2
AB - For the near-stall and fully stalled regime, where separation control is of interest, a limited amount of wing movement is always present. This is especially the case for high aspect ratio wings that exhibit some degree of structural flexibility such as seen on the X-56A. For the airfoil of the X-56A, wing section simulations were carried out for chord-based Reynolds numbers of Re=100,000 and 200,000. Below static stall (α≤12deg) a laminar separation bubble forms that gradually moves upstream towards the leading edge as the angle of attack is increased. When the wing section is subjected to high frequency plunging motions (2
UR - http://www.scopus.com/inward/record.url?scp=85086689521&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85086689521&partnerID=8YFLogxK
U2 - 10.2514/6.2016-3947
DO - 10.2514/6.2016-3947
M3 - Conference contribution
AN - SCOPUS:85086689521
SN - 9781624104367
T3 - 46th AIAA Fluid Dynamics Conference
BT - 46th AIAA Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 46th AIAA Fluid Dynamics Conference, 2016
Y2 - 13 June 2016 through 17 June 2016
ER -