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

D. Adair, W. C. Horne

Research output: Contribution to journalArticle

9 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 languageEnglish
Pages (from-to)531-541
Number of pages11
JournalEXP. FLUIDS
Volume7
Issue number8
DOIs
Publication statusPublished - Sep 1989
Externally publishedYes

Fingerprint

separated flow
airfoils
Airfoils
Turbulent flow
Boundary layers
trailing edge flaps
boundary layer separation
flow characteristics
suction
wind tunnels
Merging
Mach number
slots
wakes
Wind tunnels
NASA
boundary layers
Reynolds number
configurations

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 journalArticle

Adair, D. ; Horne, W. C. / Turbulent separated flow over and downstream of a two-element airfoil. In: EXP. FLUIDS. 1989 ; Vol. 7, No. 8. pp. 531-541.
@article{158cb49973d54598b591d8da5fb5457a,
title = "Turbulent separated flow over and downstream of a two-element airfoil",
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.",
author = "D. Adair and Horne, {W. C.}",
year = "1989",
month = "9",
doi = "10.1007/BF00187404",
language = "English",
volume = "7",
pages = "531--541",
journal = "Experiments in Fluids",
issn = "0723-4864",
publisher = "Springer Verlag",
number = "8",

}

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

UR - http://www.scopus.com/inward/citedby.url?scp=0024901618&partnerID=8YFLogxK

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 -