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 | Mineralium Deposita |
| Volume | 28 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - Jul 1993 |
| Externally published | Yes |
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ASJC Scopus subject areas
- Geophysics
- Geochemistry and Petrology
Cite this
Turbulent separated flow over and downstream of a two-element airfoil. / Adair, D.; Horne, W. C.
In: Mineralium Deposita, Vol. 28, No. 4, 07.1993, 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 - 1993/7
Y1 - 1993/7
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=34250081279&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34250081279&partnerID=8YFLogxK
U2 - 10.1007/BF00624682
DO - 10.1007/BF00624682
M3 - Article
AN - SCOPUS:34250081279
VL - 28
SP - 531
EP - 541
JO - Mineralium Deposita
JF - Mineralium Deposita
SN - 0026-4598
IS - 4
ER -