Numerical simulation of wing section near stall

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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<k<4) coherent structures form above the suction surface. A low-frequency plunging motion (k=0.7) on the other hand results in a periodic growing and shrinking of the suction side trailing edge separation and an intermittent shedding of coherent structures. The simulation data for the latter are in reasonable agreement with University of Arizona wind tunnel data. Static wing section simulations for α=15deg revealed a periodic bursting of a laminar leading edge bubble with a dimensionless frequency of f≈0.07 and large lift and drag coefficient fluctuations. Based on a Proper Orthogonal Decomposition of the unsteady flow data three-dimensional modes with spanwise wavelengths of 80% and more of the chord length were identified.

Original languageEnglish (US)
Title of host publication46th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104367
StatePublished - 2016
Event46th AIAA Fluid Dynamics Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Other

Other46th AIAA Fluid Dynamics Conference, 2016
CountryUnited States
CityWashington
Period6/13/166/17/16

Fingerprint

Computer simulation
Drag coefficient
Unsteady flow
Angle of attack
Airfoils
Wind tunnels
Aspect ratio
Reynolds number
Decomposition
Wavelength

ASJC Scopus subject areas

  • Engineering (miscellaneous)
  • Aerospace Engineering

Cite this

Gross, A., Little, J. C., & Fasel, H. F. (2016). Numerical simulation of wing section near stall. In 46th AIAA Fluid Dynamics Conference American Institute of Aeronautics and Astronautics Inc, AIAA.

Numerical simulation of wing section near stall. / Gross, A.; Little, Jesse C; Fasel, Hermann F.

46th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Gross, A, Little, JC & Fasel, HF 2016, Numerical simulation of wing section near stall. in 46th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 46th AIAA Fluid Dynamics Conference, 2016, Washington, United States, 6/13/16.
Gross A, Little JC, Fasel HF. Numerical simulation of wing section near stall. In 46th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 2016
Gross, A. ; Little, Jesse C ; Fasel, Hermann F. / Numerical simulation of wing section near stall. 46th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016.
@inproceedings{60815ec79a3e40028d372a57e88a6cf4,
title = "Numerical simulation of wing section near stall",
abstract = "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",
author = "A. Gross and Little, {Jesse C} and Fasel, {Hermann F}",
year = "2016",
language = "English (US)",
isbn = "9781624104367",
booktitle = "46th AIAA Fluid Dynamics Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

}

TY - GEN

T1 - Numerical simulation of wing section near stall

AU - Gross, A.

AU - Little, Jesse C

AU - Fasel, Hermann F

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=84980374209&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84980374209&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84980374209

SN - 9781624104367

BT - 46th AIAA Fluid Dynamics Conference

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -