Abstract
A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M∞ = 1.3 and M ∞ = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.
| Original language | English |
|---|---|
| Title of host publication | Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting |
| Pages | 10486-10497 |
| Number of pages | 12 |
| Publication status | Published - Dec 1 2006 |
| Externally published | Yes |
| Event | 44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States Duration: Jan 9 2006 → Jan 12 2006 |
Publication series
| Name | Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting |
|---|---|
| Volume | 14 |
Conference
| Conference | 44th AIAA Aerospace Sciences Meeting 2006 |
|---|---|
| Country | United States |
| City | Reno, NV |
| Period | 1/9/06 → 1/12/06 |
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All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering
Cite this
Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. / Ogawa, Hideaki; Babinsky, H.
Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. 2006. p. 10486-10497 (Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting; Vol. 14).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Experimental investigation of 3D shock / boundary layer interaction control in transonic flows
AU - Ogawa, Hideaki
AU - Babinsky, H.
PY - 2006/12/1
Y1 - 2006/12/1
N2 - A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M∞ = 1.3 and M ∞ = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.
AB - A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M∞ = 1.3 and M ∞ = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.
UR - http://www.scopus.com/inward/record.url?scp=34250730718&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34250730718&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34250730718
SN - 1563478072
SN - 9781563478079
T3 - Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
SP - 10486
EP - 10497
BT - Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
ER -