Abstract
Flow characteristics in the vicinity of the flap of a single-slotted airfoil are presented and analysed. The flow remained attached over the model surfaces except in the vicinity of the flap trailing edge where a small region of boundary-layer separation extended over the aft 7% of flap chord. The airfoil configuration was tested at a Mach number of 0.09 and a chord Reynolds number of 1.8 × 106 in the NASA Ames Research Center 7- by 10-Foot Wind Tunnel. The flow was complicated by the presence of a strong, initially inviscid, jet, emanating from the slot between airfoil and flap, and a gradual merging of the main airfoil wake and flap suction-side boundary layer.
| Original language | English |
|---|---|
| Pages (from-to) | 531-541 |
| Number of pages | 11 |
| Journal | EXP. FLUIDS |
| Volume | 7 |
| Issue number | 8 |
| DOIs | |
| Publication status | Published - Sep 1989 |
| Externally published | Yes |
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ASJC Scopus subject areas
- Mechanics of Materials
- Mechanical Engineering
- Computational Mechanics
- Fluid Flow and Transfer Processes
Cite this
Turbulent separated flow over and downstream of a two-element airfoil. / Adair, D.; Horne, W. C.
In: EXP. FLUIDS, Vol. 7, No. 8, 09.1989, p. 531-541.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Turbulent separated flow over and downstream of a two-element airfoil
AU - Adair, D.
AU - Horne, W. C.
PY - 1989/9
Y1 - 1989/9
N2 - Flow characteristics in the vicinity of the flap of a single-slotted airfoil are presented and analysed. The flow remained attached over the model surfaces except in the vicinity of the flap trailing edge where a small region of boundary-layer separation extended over the aft 7% of flap chord. The airfoil configuration was tested at a Mach number of 0.09 and a chord Reynolds number of 1.8 × 106 in the NASA Ames Research Center 7- by 10-Foot Wind Tunnel. The flow was complicated by the presence of a strong, initially inviscid, jet, emanating from the slot between airfoil and flap, and a gradual merging of the main airfoil wake and flap suction-side boundary layer.
AB - Flow characteristics in the vicinity of the flap of a single-slotted airfoil are presented and analysed. The flow remained attached over the model surfaces except in the vicinity of the flap trailing edge where a small region of boundary-layer separation extended over the aft 7% of flap chord. The airfoil configuration was tested at a Mach number of 0.09 and a chord Reynolds number of 1.8 × 106 in the NASA Ames Research Center 7- by 10-Foot Wind Tunnel. The flow was complicated by the presence of a strong, initially inviscid, jet, emanating from the slot between airfoil and flap, and a gradual merging of the main airfoil wake and flap suction-side boundary layer.
UR - http://www.scopus.com/inward/record.url?scp=0024901618&partnerID=8YFLogxK
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U2 - 10.1007/BF00187404
DO - 10.1007/BF00187404
M3 - Article
VL - 7
SP - 531
EP - 541
JO - Experiments in Fluids
JF - Experiments in Fluids
SN - 0723-4864
IS - 8
ER -