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 | Experiments in Fluids |
| Volume | 7 |
| Issue number | 8 |
| DOIs | |
| Publication status | Published - Sep 1 1989 |
| Externally published | Yes |
ASJC Scopus subject areas
- Computational Mechanics
- Mechanics of Materials
- Physics and Astronomy(all)
- Fluid Flow and Transfer Processes
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Adair, D., & Horne, W. C. (1989). Turbulent separated flow over and downstream of a two-element airfoil. Experiments in Fluids, 7(8), 531-541. https://doi.org/10.1007/BF00187404