Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number

Jian Ye; Zhengping Zou; Lipeng Lu; Lin Yang

Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number

Jian Ye^*
, Zhengping Zou
, Lipeng Lu
, Lin Yang

^*Corresponding author for this work

Research institute of Aero-Engine

Beihang University

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

12 Scopus citations

Abstract

A direct numerical simulation (DNS) around a 2-D airfoil was carried out through high order finite difference scheme, the Reynolds number based on chord is 1.0×10⁴, the angle of attack is 3°. Via analyzing the quasi-periodic numerical solutions, the separation mechanism of leading edge flow at low Reynolds number was investigated, and the rules of vortices interaction were summarized. Numerical results indicate that there exists suction spike on airfoil near elliptical leading edge, separation occurs on the effect of strongly adverse pressure gradient of suction spike. Vortices structure including primary vortex, shed vortex and secondary vortex forms on the airfoil surface, its scale varies with time and it is absolutely unsteady. Surface pressure distribution can be used to describe the airfoil boundary layer flow well.

Original language	English
Pages (from-to)	693-697
Number of pages	5
Journal	Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
Volume	30
Issue number	8
State	Published - Aug 2004

Keywords

Airfoil
Direct numerical simulation
Low Reynolds number
Nonsteady flow
Separation

Cite this

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title = "Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number",

abstract = "A direct numerical simulation (DNS) around a 2-D airfoil was carried out through high order finite difference scheme, the Reynolds number based on chord is 1.0×104, the angle of attack is 3°. Via analyzing the quasi-periodic numerical solutions, the separation mechanism of leading edge flow at low Reynolds number was investigated, and the rules of vortices interaction were summarized. Numerical results indicate that there exists suction spike on airfoil near elliptical leading edge, separation occurs on the effect of strongly adverse pressure gradient of suction spike. Vortices structure including primary vortex, shed vortex and secondary vortex forms on the airfoil surface, its scale varies with time and it is absolutely unsteady. Surface pressure distribution can be used to describe the airfoil boundary layer flow well.",

keywords = "Airfoil, Direct numerical simulation, Low Reynolds number, Nonsteady flow, Separation",

author = "Jian Ye and Zhengping Zou and Lipeng Lu and Lin Yang",

year = "2004",

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language = "英语",

volume = "30",

pages = "693--697",

journal = "Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics",

issn = "1001-5965",

publisher = "Beijing University of Aeronautics and Astronautics (BUAA)",

number = "8",

}

TY - JOUR

T1 - Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number

AU - Ye, Jian

AU - Zou, Zhengping

AU - Lu, Lipeng

AU - Yang, Lin

PY - 2004/8

Y1 - 2004/8

N2 - A direct numerical simulation (DNS) around a 2-D airfoil was carried out through high order finite difference scheme, the Reynolds number based on chord is 1.0×104, the angle of attack is 3°. Via analyzing the quasi-periodic numerical solutions, the separation mechanism of leading edge flow at low Reynolds number was investigated, and the rules of vortices interaction were summarized. Numerical results indicate that there exists suction spike on airfoil near elliptical leading edge, separation occurs on the effect of strongly adverse pressure gradient of suction spike. Vortices structure including primary vortex, shed vortex and secondary vortex forms on the airfoil surface, its scale varies with time and it is absolutely unsteady. Surface pressure distribution can be used to describe the airfoil boundary layer flow well.

AB - A direct numerical simulation (DNS) around a 2-D airfoil was carried out through high order finite difference scheme, the Reynolds number based on chord is 1.0×104, the angle of attack is 3°. Via analyzing the quasi-periodic numerical solutions, the separation mechanism of leading edge flow at low Reynolds number was investigated, and the rules of vortices interaction were summarized. Numerical results indicate that there exists suction spike on airfoil near elliptical leading edge, separation occurs on the effect of strongly adverse pressure gradient of suction spike. Vortices structure including primary vortex, shed vortex and secondary vortex forms on the airfoil surface, its scale varies with time and it is absolutely unsteady. Surface pressure distribution can be used to describe the airfoil boundary layer flow well.

KW - Airfoil

KW - Direct numerical simulation

KW - Low Reynolds number

KW - Nonsteady flow

KW - Separation

UR - https://www.scopus.com/pages/publications/10044224789

M3 - 文章

AN - SCOPUS:10044224789

SN - 1001-5965

VL - 30

SP - 693

EP - 697

JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

IS - 8

ER -

Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number

Abstract

Keywords

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