Effective flow control for rotorcraft applications at flight mach mumbers (invited)

Hassan Nagib, John Kiedaisch, David Greenblatt, Israel J Wygnanski, Ahmed Hassan

Research output: Chapter in Book/Report/Conference proceedingConference contribution

26 Citations (Scopus)

Abstract

Pulsating zero-mass flux jets introduced from spanwise slots at various locations on the upper surface of an oscillating VR-7 airfoil model are shown to be effective in controlling lift, moment and drag coefficients over the range of Mach numbers from 0.1 to 0.4. This control is demonstrated over a wide range of mean angles of attack of the oscillating airfoil from light to deep stall conditions. Maintaining the nondimensional frequency and amplitude of the forcing unchanged results in comparable modifications of the aerodynamic coefficients throughout this Mach number range. Therefore, it appears that this active-flow control technique is only limited by the ability to generate the adequate forcing conditions at the higher Mach numbers required for applications such as rotorcraft.

Original languageEnglish (US)
Title of host publication15th AIAA Computational Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
StatePublished - 2001
Event15th AIAA Computational Fluid Dynamics Conference 2001 - Anaheim, CA, United States
Duration: Jun 11 2001Jun 14 2001

Other

Other15th AIAA Computational Fluid Dynamics Conference 2001
CountryUnited States
CityAnaheim, CA
Period6/11/016/14/01

Fingerprint

Flow control
Mach number
Airfoils
Drag coefficient
Angle of attack
Aerodynamics
Mass transfer

ASJC Scopus subject areas

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

Cite this

Nagib, H., Kiedaisch, J., Greenblatt, D., Wygnanski, I. J., & Hassan, A. (2001). Effective flow control for rotorcraft applications at flight mach mumbers (invited). In 15th AIAA Computational Fluid Dynamics Conference American Institute of Aeronautics and Astronautics Inc..

Effective flow control for rotorcraft applications at flight mach mumbers (invited). / Nagib, Hassan; Kiedaisch, John; Greenblatt, David; Wygnanski, Israel J; Hassan, Ahmed.

15th AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc., 2001.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Nagib, H, Kiedaisch, J, Greenblatt, D, Wygnanski, IJ & Hassan, A 2001, Effective flow control for rotorcraft applications at flight mach mumbers (invited). in 15th AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc., 15th AIAA Computational Fluid Dynamics Conference 2001, Anaheim, CA, United States, 6/11/01.
Nagib H, Kiedaisch J, Greenblatt D, Wygnanski IJ, Hassan A. Effective flow control for rotorcraft applications at flight mach mumbers (invited). In 15th AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc. 2001
Nagib, Hassan ; Kiedaisch, John ; Greenblatt, David ; Wygnanski, Israel J ; Hassan, Ahmed. / Effective flow control for rotorcraft applications at flight mach mumbers (invited). 15th AIAA Computational Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc., 2001.
@inproceedings{70e45b82a9ec4039827a27f7a6d4a325,
title = "Effective flow control for rotorcraft applications at flight mach mumbers (invited)",
abstract = "Pulsating zero-mass flux jets introduced from spanwise slots at various locations on the upper surface of an oscillating VR-7 airfoil model are shown to be effective in controlling lift, moment and drag coefficients over the range of Mach numbers from 0.1 to 0.4. This control is demonstrated over a wide range of mean angles of attack of the oscillating airfoil from light to deep stall conditions. Maintaining the nondimensional frequency and amplitude of the forcing unchanged results in comparable modifications of the aerodynamic coefficients throughout this Mach number range. Therefore, it appears that this active-flow control technique is only limited by the ability to generate the adequate forcing conditions at the higher Mach numbers required for applications such as rotorcraft.",
author = "Hassan Nagib and John Kiedaisch and David Greenblatt and Wygnanski, {Israel J} and Ahmed Hassan",
year = "2001",
language = "English (US)",
booktitle = "15th AIAA Computational Fluid Dynamics Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc.",

}

TY - GEN

T1 - Effective flow control for rotorcraft applications at flight mach mumbers (invited)

AU - Nagib, Hassan

AU - Kiedaisch, John

AU - Greenblatt, David

AU - Wygnanski, Israel J

AU - Hassan, Ahmed

PY - 2001

Y1 - 2001

N2 - Pulsating zero-mass flux jets introduced from spanwise slots at various locations on the upper surface of an oscillating VR-7 airfoil model are shown to be effective in controlling lift, moment and drag coefficients over the range of Mach numbers from 0.1 to 0.4. This control is demonstrated over a wide range of mean angles of attack of the oscillating airfoil from light to deep stall conditions. Maintaining the nondimensional frequency and amplitude of the forcing unchanged results in comparable modifications of the aerodynamic coefficients throughout this Mach number range. Therefore, it appears that this active-flow control technique is only limited by the ability to generate the adequate forcing conditions at the higher Mach numbers required for applications such as rotorcraft.

AB - Pulsating zero-mass flux jets introduced from spanwise slots at various locations on the upper surface of an oscillating VR-7 airfoil model are shown to be effective in controlling lift, moment and drag coefficients over the range of Mach numbers from 0.1 to 0.4. This control is demonstrated over a wide range of mean angles of attack of the oscillating airfoil from light to deep stall conditions. Maintaining the nondimensional frequency and amplitude of the forcing unchanged results in comparable modifications of the aerodynamic coefficients throughout this Mach number range. Therefore, it appears that this active-flow control technique is only limited by the ability to generate the adequate forcing conditions at the higher Mach numbers required for applications such as rotorcraft.

UR - http://www.scopus.com/inward/record.url?scp=84900014053&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84900014053&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84900014053

BT - 15th AIAA Computational Fluid Dynamics Conference

PB - American Institute of Aeronautics and Astronautics Inc.

ER -