Abstract
Three-dimensional bumps have been developed and investigated on transonic wings, aiming to fulfill two major objectives of shock-wave/boundary-layer interaction control, that is, drag reduction and buffet delay. An experimental investigation has been conducted for a rounded bump in channel flow at the University of Cambridge and a computational study has been performed for a spanwise series of rounded bumps mounted on a transonic aerofoil at the University of Stuttgart. In both cases wave drag reduction and mild control effects on the boundary layer have been observed. Control effectiveness has been assessed for various bump configurations. A double configuration of narrow rounded bumps has been found to perform best, considerably reducing wave drag by means of a well-established λ-shock structure with little viscous penalty and thus achieving a maximum overall drag reduction of about 30 %, especially when significant wave drag is present Counter-rotating stream wise vortex pairs have been produced by some configurations as a result of local flow separation. On the whole a large potential of three-dimensional control with discrete rounded bumps has been demonstrated both experimentally and numerically.
| Original language | English |
|---|---|
| Pages (from-to) | 1442-1452 |
| Number of pages | 11 |
| Journal | AIAA journal |
| Volume | 46 |
| Issue number | 6 |
| DOIs | |
| Publication status | Published - Jun 1 2008 |
| Externally published | Yes |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
Cite this
Shock-wave/boundary-layer interaction control using three-dimensional bumps for transonic wings. / Ogawa, H.; Babinsky, H.; M. Pätzold, Pätzold; T. Lutz, Lutz.
In: AIAA journal, Vol. 46, No. 6, 01.06.2008, p. 1442-1452.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Shock-wave/boundary-layer interaction control using three-dimensional bumps for transonic wings
AU - Ogawa, H.
AU - Babinsky, H.
AU - M. Pätzold, Pätzold
AU - T. Lutz, Lutz
PY - 2008/6/1
Y1 - 2008/6/1
N2 - Three-dimensional bumps have been developed and investigated on transonic wings, aiming to fulfill two major objectives of shock-wave/boundary-layer interaction control, that is, drag reduction and buffet delay. An experimental investigation has been conducted for a rounded bump in channel flow at the University of Cambridge and a computational study has been performed for a spanwise series of rounded bumps mounted on a transonic aerofoil at the University of Stuttgart. In both cases wave drag reduction and mild control effects on the boundary layer have been observed. Control effectiveness has been assessed for various bump configurations. A double configuration of narrow rounded bumps has been found to perform best, considerably reducing wave drag by means of a well-established λ-shock structure with little viscous penalty and thus achieving a maximum overall drag reduction of about 30 %, especially when significant wave drag is present Counter-rotating stream wise vortex pairs have been produced by some configurations as a result of local flow separation. On the whole a large potential of three-dimensional control with discrete rounded bumps has been demonstrated both experimentally and numerically.
AB - Three-dimensional bumps have been developed and investigated on transonic wings, aiming to fulfill two major objectives of shock-wave/boundary-layer interaction control, that is, drag reduction and buffet delay. An experimental investigation has been conducted for a rounded bump in channel flow at the University of Cambridge and a computational study has been performed for a spanwise series of rounded bumps mounted on a transonic aerofoil at the University of Stuttgart. In both cases wave drag reduction and mild control effects on the boundary layer have been observed. Control effectiveness has been assessed for various bump configurations. A double configuration of narrow rounded bumps has been found to perform best, considerably reducing wave drag by means of a well-established λ-shock structure with little viscous penalty and thus achieving a maximum overall drag reduction of about 30 %, especially when significant wave drag is present Counter-rotating stream wise vortex pairs have been produced by some configurations as a result of local flow separation. On the whole a large potential of three-dimensional control with discrete rounded bumps has been demonstrated both experimentally and numerically.
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UR - http://www.scopus.com/inward/citedby.url?scp=45849086102&partnerID=8YFLogxK
U2 - 10.2514/1.32049
DO - 10.2514/1.32049
M3 - Article
AN - SCOPUS:45849086102
VL - 46
SP - 1442
EP - 1452
JO - AIAA Journal
JF - AIAA Journal
SN - 0001-1452
IS - 6
ER -