Active control of shock/boundary layer interaction in transonic flow over airfoils

J. L. Vadillo; R. K. Agarwal; A. A. Hassan

doi:10.2514/6.2005-486

Active control of shock/boundary layer interaction in transonic flow over airfoils

J. L. Vadillo, R. K. Agarwal, A. A. Hassan

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

4 Scopus citations

Abstract

The objective of this paper is to evaluate, via numerical simulation, the feasibility of controlling the shock/boundary layer (SBL) interaction on airfoils in transonic flow thereby weakening the shock wave(s) and reducing the pockets of supersonic regions using an oscillatory zero-net-mass jet actuator and thus achieving the desired changes in aerodynamic forces and moments. It is shown that by properly choosing the amplitude, frequency, and location of an oscillatory zero-net-mass jet on the airfoil surface, desired modulation in lift, drag and pitching moment coefficients can be obtained for a given freestream Mach number, Reynolds number and angle of attack. Results from these calculations indicate the possibility of "hingeless" aerospace vehicle attitude control in the future using active flow control (AFC).

Original language	English
Pages	2319-2328
Number of pages	10
DOIs	https://doi.org/10.2514/6.2005-486
State	Published - 2005
Event	43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 10 2005 → Jan 13 2005

Conference

Conference	43rd AIAA Aerospace Sciences Meeting and Exhibit
Country/Territory	United States
City	Reno, NV
Period	01/10/05 → 01/13/05

Access to Document

10.2514/6.2005-486

Cite this

@conference{0574ae05df16478da5a1679b4c745eb7,

title = "Active control of shock/boundary layer interaction in transonic flow over airfoils",

abstract = "The objective of this paper is to evaluate, via numerical simulation, the feasibility of controlling the shock/boundary layer (SBL) interaction on airfoils in transonic flow thereby weakening the shock wave(s) and reducing the pockets of supersonic regions using an oscillatory zero-net-mass jet actuator and thus achieving the desired changes in aerodynamic forces and moments. It is shown that by properly choosing the amplitude, frequency, and location of an oscillatory zero-net-mass jet on the airfoil surface, desired modulation in lift, drag and pitching moment coefficients can be obtained for a given freestream Mach number, Reynolds number and angle of attack. Results from these calculations indicate the possibility of {"}hingeless{"} aerospace vehicle attitude control in the future using active flow control (AFC).",

author = "Vadillo, {J. L.} and Agarwal, {R. K.} and Hassan, {A. A.}",

year = "2005",

doi = "10.2514/6.2005-486",

language = "English",

pages = "2319--2328",

note = "43rd AIAA Aerospace Sciences Meeting and Exhibit ; Conference date: 10-01-2005 Through 13-01-2005",

}

TY - CONF

T1 - Active control of shock/boundary layer interaction in transonic flow over airfoils

AU - Vadillo, J. L.

AU - Agarwal, R. K.

AU - Hassan, A. A.

PY - 2005

Y1 - 2005

N2 - The objective of this paper is to evaluate, via numerical simulation, the feasibility of controlling the shock/boundary layer (SBL) interaction on airfoils in transonic flow thereby weakening the shock wave(s) and reducing the pockets of supersonic regions using an oscillatory zero-net-mass jet actuator and thus achieving the desired changes in aerodynamic forces and moments. It is shown that by properly choosing the amplitude, frequency, and location of an oscillatory zero-net-mass jet on the airfoil surface, desired modulation in lift, drag and pitching moment coefficients can be obtained for a given freestream Mach number, Reynolds number and angle of attack. Results from these calculations indicate the possibility of "hingeless" aerospace vehicle attitude control in the future using active flow control (AFC).

AB - The objective of this paper is to evaluate, via numerical simulation, the feasibility of controlling the shock/boundary layer (SBL) interaction on airfoils in transonic flow thereby weakening the shock wave(s) and reducing the pockets of supersonic regions using an oscillatory zero-net-mass jet actuator and thus achieving the desired changes in aerodynamic forces and moments. It is shown that by properly choosing the amplitude, frequency, and location of an oscillatory zero-net-mass jet on the airfoil surface, desired modulation in lift, drag and pitching moment coefficients can be obtained for a given freestream Mach number, Reynolds number and angle of attack. Results from these calculations indicate the possibility of "hingeless" aerospace vehicle attitude control in the future using active flow control (AFC).

UR - http://www.scopus.com/inward/record.url?scp=30744443864&partnerID=8YFLogxK

U2 - 10.2514/6.2005-486

DO - 10.2514/6.2005-486

M3 - Paper

AN - SCOPUS:30744443864

SP - 2319

EP - 2328

T2 - 43rd AIAA Aerospace Sciences Meeting and Exhibit

Y2 - 10 January 2005 through 13 January 2005

ER -

Active control of shock/boundary layer interaction in transonic flow over airfoils

Abstract

Conference

Access to Document

Other files and links

Fingerprint

Cite this