Abstract
Drag reduction by means of flow control is investigated for supersonic base flows at Mach number M = 2.46 using Direct Numerical Simulations (DNS) and the Flow Simulation Methodology (FSM). The objective of the present work is to understand the evolution of coherent structures in the flow and how flow control techniques modify these structures. For such investigations, simulation methods that capture the dynamics of the large turbulent structures are required. For transitional base flows at ReD = 30,000 DNS are performed. Due to the drastically increased computational cost of DNS at higher Reynolds numbers, a hybrid RANS/LES method (FSM) is applied to simulate base flows with flow control at ReD = 100,000. Active and passive flow control techniques that alter the near-wake by introducing axisymmetric and longitudinal perturbations are investigated. A detailed analysis of the dynamics of the resulting turbulent (coherent) structures is presented.
| Original language | English (US) |
|---|---|
| Title of host publication | Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting |
| Pages | 5685-5696 |
| Number of pages | 12 |
| Volume | 8 |
| State | Published - 2006 |
| Event | 44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States Duration: Jan 9 2006 → Jan 12 2006 |
Other
| Other | 44th AIAA Aerospace Sciences Meeting 2006 |
|---|---|
| Country | United States |
| City | Reno, NV |
| Period | 1/9/06 → 1/12/06 |
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ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
Cite this
Numerical investigation of transitional supersonic base flows with flow control. / Sivasubramanian, Jayahar; Sandberg, Richard D.; Von Terzi, Dominic A.; Fasel, Hermann F.
Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 8 2006. p. 5685-5696.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Numerical investigation of transitional supersonic base flows with flow control
AU - Sivasubramanian, Jayahar
AU - Sandberg, Richard D.
AU - Von Terzi, Dominic A.
AU - Fasel, Hermann F
PY - 2006
Y1 - 2006
N2 - Drag reduction by means of flow control is investigated for supersonic base flows at Mach number M = 2.46 using Direct Numerical Simulations (DNS) and the Flow Simulation Methodology (FSM). The objective of the present work is to understand the evolution of coherent structures in the flow and how flow control techniques modify these structures. For such investigations, simulation methods that capture the dynamics of the large turbulent structures are required. For transitional base flows at ReD = 30,000 DNS are performed. Due to the drastically increased computational cost of DNS at higher Reynolds numbers, a hybrid RANS/LES method (FSM) is applied to simulate base flows with flow control at ReD = 100,000. Active and passive flow control techniques that alter the near-wake by introducing axisymmetric and longitudinal perturbations are investigated. A detailed analysis of the dynamics of the resulting turbulent (coherent) structures is presented.
AB - Drag reduction by means of flow control is investigated for supersonic base flows at Mach number M = 2.46 using Direct Numerical Simulations (DNS) and the Flow Simulation Methodology (FSM). The objective of the present work is to understand the evolution of coherent structures in the flow and how flow control techniques modify these structures. For such investigations, simulation methods that capture the dynamics of the large turbulent structures are required. For transitional base flows at ReD = 30,000 DNS are performed. Due to the drastically increased computational cost of DNS at higher Reynolds numbers, a hybrid RANS/LES method (FSM) is applied to simulate base flows with flow control at ReD = 100,000. Active and passive flow control techniques that alter the near-wake by introducing axisymmetric and longitudinal perturbations are investigated. A detailed analysis of the dynamics of the resulting turbulent (coherent) structures is presented.
UR - http://www.scopus.com/inward/record.url?scp=34347225920&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34347225920&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34347225920
SN - 1563478072
SN - 9781563478079
VL - 8
SP - 5685
EP - 5696
BT - Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
ER -