Turbulent separated flow over and downstream of a two-element airfoil

D. Adair; W. C. Horne

doi:10.1007/BF00187404

Turbulent separated flow over and downstream of a two-element airfoil

D. Adair, W. C. Horne

Research output: Contribution to journal › Article › peer-review

10 Citations (Scopus)

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	https://doi.org/10.1007/BF00187404
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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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.

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