Numerical investigation of compressibility effects on active control of boundary layer separation

Daniel M. Israel; Hermann F. Fasel

doi:10.2514/6.2001-2771

Numerical investigation of compressibility effects on active control of boundary layer separation

Daniel M. Israel, Hermann F. Fasel

Aerospace and Mechanical Engineering

Research output: Contribution to conference › Paper › peer-review

3 Scopus citations

Abstract

Active flow control (AFC) as a method of separation control was investigated for laminar flow over a curved wall. Experimental research has demonstrated that AFC using periodic suction and blowing is an extremely efficient way to suppress or weaken separation. However, there is a lack of accurate computational data for this flow. We applied CFD to investigate the experimental geometry of Seifert and Pack (1999), which consists of the top surface of an airfoil mounted on the side wall of the 0.3-meter cryogenic wind tunnel at NASA Langley Research Center. We used an high order finite-difference code to simulate laminar flow at a Reynolds number of Re_c = 10⁴ and Mach numbers of 0.25 and 0.65. The effects of forcing frequency and amplitude were investigated, as well as effects of compressibility.

Original language	English (US)
DOIs	https://doi.org/10.2514/6.2001-2771
State	Published - 2001
Event	15th AIAA Computational Fluid Dynamics Conference 2001 - Anaheim, CA, United States Duration: Jun 11 2001 → Jun 14 2001

Other

Other	15th AIAA Computational Fluid Dynamics Conference 2001
Country/Territory	United States
City	Anaheim, CA
Period	6/11/01 → 6/14/01

ASJC Scopus subject areas

Fluid Flow and Transfer Processes
Energy Engineering and Power Technology
Aerospace Engineering
Mechanical Engineering

Access to Document

10.2514/6.2001-2771

Cite this

@conference{48ab5fb59ded47c9a3c45038c6b70f02,

title = "Numerical investigation of compressibility effects on active control of boundary layer separation",

abstract = "Active flow control (AFC) as a method of separation control was investigated for laminar flow over a curved wall. Experimental research has demonstrated that AFC using periodic suction and blowing is an extremely efficient way to suppress or weaken separation. However, there is a lack of accurate computational data for this flow. We applied CFD to investigate the experimental geometry of Seifert and Pack (1999), which consists of the top surface of an airfoil mounted on the side wall of the 0.3-meter cryogenic wind tunnel at NASA Langley Research Center. We used an high order finite-difference code to simulate laminar flow at a Reynolds number of Rec = 104 and Mach numbers of 0.25 and 0.65. The effects of forcing frequency and amplitude were investigated, as well as effects of compressibility.",

author = "Israel, {Daniel M.} and Fasel, {Hermann F.}",

year = "2001",

doi = "10.2514/6.2001-2771",

language = "English (US)",

note = "15th AIAA Computational Fluid Dynamics Conference 2001 ; Conference date: 11-06-2001 Through 14-06-2001",

}

TY - CONF

T1 - Numerical investigation of compressibility effects on active control of boundary layer separation

AU - Israel, Daniel M.

AU - Fasel, Hermann F.

PY - 2001

Y1 - 2001

N2 - Active flow control (AFC) as a method of separation control was investigated for laminar flow over a curved wall. Experimental research has demonstrated that AFC using periodic suction and blowing is an extremely efficient way to suppress or weaken separation. However, there is a lack of accurate computational data for this flow. We applied CFD to investigate the experimental geometry of Seifert and Pack (1999), which consists of the top surface of an airfoil mounted on the side wall of the 0.3-meter cryogenic wind tunnel at NASA Langley Research Center. We used an high order finite-difference code to simulate laminar flow at a Reynolds number of Rec = 104 and Mach numbers of 0.25 and 0.65. The effects of forcing frequency and amplitude were investigated, as well as effects of compressibility.

AB - Active flow control (AFC) as a method of separation control was investigated for laminar flow over a curved wall. Experimental research has demonstrated that AFC using periodic suction and blowing is an extremely efficient way to suppress or weaken separation. However, there is a lack of accurate computational data for this flow. We applied CFD to investigate the experimental geometry of Seifert and Pack (1999), which consists of the top surface of an airfoil mounted on the side wall of the 0.3-meter cryogenic wind tunnel at NASA Langley Research Center. We used an high order finite-difference code to simulate laminar flow at a Reynolds number of Rec = 104 and Mach numbers of 0.25 and 0.65. The effects of forcing frequency and amplitude were investigated, as well as effects of compressibility.

UR - http://www.scopus.com/inward/record.url?scp=85086615495&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85086615495&partnerID=8YFLogxK

U2 - 10.2514/6.2001-2771

DO - 10.2514/6.2001-2771

M3 - Paper

AN - SCOPUS:85086615495

T2 - 15th AIAA Computational Fluid Dynamics Conference 2001

Y2 - 11 June 2001 through 14 June 2001

ER -

Numerical investigation of compressibility effects on active control of boundary layer separation

Abstract

Other

ASJC Scopus subject areas

Access to Document

Other files and links

Fingerprint

Cite this