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CFD simulation of momentum injection control past a streamlined body

CFD simulation of momentum injection control past a streamlined body Purpose – The purpose of this paper is to achieve high‐performance aerofoils that enable delayed stall conditions and achieve high lift to drag ratios. Design/methodology/approach – The unsteady Reynolds averaged Navier‐Stokes equations are employed in conjunction with a shear stress transport ( κ‐ω ) turbulence model. A control equation is designed and implemented to determine the temporal response of the actuator. A rotating element, in the form of an actuator disc, is embedded on the leading edge of NACA 0012 aerofoil, to inject momentum into the wake region. The actuator disc is rotated at different angular speeds, for angles of attack ( α ) between 00 and 240. Findings – Phenomena such as flow separation, wake vortices, delayed stall, wake control, etc. are numerically investigated by means of streamlines, streaklines, isobars, etc. Streamwise and cross‐stream forces on the aerofoil are obtained. The influence of momentum injection parameter ( ξ ) on the fluid flow patterns, and hence on the forces acting on the streamlined body are determined. A synchronization‐based coupling scheme is designed and implemented to achieve annihilation of wake vortices. A delayed stall angle resulted with an attendant increase in maximum lift coefficient. Due to delay and/or prevention of separation, drag coefficient is also reduced considerably, resulting in a high‐performance lifting surface. Research limitations/implications – The practicality of momentum injection principle requires both wide ranging and intensive further studies to move forward beyond the proof of concept stage. Practical implications – Determination of forces and moments on an aerofoil is of vital interest in aero‐dynamic design. Perhaps, runways of the future can be shorter and/or more pay load can be carried by an aircraft, for the same stall speed. Originality/value – The paper describes how a synchronization‐based coupling scheme is designed and implemented along with the RANS solver. Furthermore, it is tested to verify the dynamic adaptability of the wake vortex annihilation for NACA 0012 aerofoils. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Numerical Methods for Heat & Fluid Flow Emerald Publishing

CFD simulation of momentum injection control past a streamlined body

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Publisher
Emerald Publishing
Copyright
Copyright © 2011 Emerald Group Publishing Limited. All rights reserved.
ISSN
0961-5539
DOI
10.1108/09615531111177750
Publisher site
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Abstract

Purpose – The purpose of this paper is to achieve high‐performance aerofoils that enable delayed stall conditions and achieve high lift to drag ratios. Design/methodology/approach – The unsteady Reynolds averaged Navier‐Stokes equations are employed in conjunction with a shear stress transport ( κ‐ω ) turbulence model. A control equation is designed and implemented to determine the temporal response of the actuator. A rotating element, in the form of an actuator disc, is embedded on the leading edge of NACA 0012 aerofoil, to inject momentum into the wake region. The actuator disc is rotated at different angular speeds, for angles of attack ( α ) between 00 and 240. Findings – Phenomena such as flow separation, wake vortices, delayed stall, wake control, etc. are numerically investigated by means of streamlines, streaklines, isobars, etc. Streamwise and cross‐stream forces on the aerofoil are obtained. The influence of momentum injection parameter ( ξ ) on the fluid flow patterns, and hence on the forces acting on the streamlined body are determined. A synchronization‐based coupling scheme is designed and implemented to achieve annihilation of wake vortices. A delayed stall angle resulted with an attendant increase in maximum lift coefficient. Due to delay and/or prevention of separation, drag coefficient is also reduced considerably, resulting in a high‐performance lifting surface. Research limitations/implications – The practicality of momentum injection principle requires both wide ranging and intensive further studies to move forward beyond the proof of concept stage. Practical implications – Determination of forces and moments on an aerofoil is of vital interest in aero‐dynamic design. Perhaps, runways of the future can be shorter and/or more pay load can be carried by an aircraft, for the same stall speed. Originality/value – The paper describes how a synchronization‐based coupling scheme is designed and implemented along with the RANS solver. Furthermore, it is tested to verify the dynamic adaptability of the wake vortex annihilation for NACA 0012 aerofoils.

Journal

International Journal of Numerical Methods for Heat & Fluid Flow – Emerald Publishing

Published: Nov 1, 2011

Keywords: Aerospace industry; Fluid dynamics; Actuators; Force measurement; Aerofoils; Momentum injection

References

  • On some control problems in fluid mechanics
    Abergel, F.; Temam, R.
  • Computational study into the flow field developed around a cascade of NACA 0012 airfoils
    Ahmed, N.; Yilbas, B.S.; Budair, M.O.
  • Flow control for an aerofoil with leading edge rotation: an experimental study
    Al‐Garni, A.Z.; Al‐Garni, A.M.; Ahemd, S.A.; Sahin, A.Z.
  • Aircraft Performance and Design
    Anderson, J.D.
  • Active management of naturally separated flow over a solid surface. Part 1. The forced reattachment process
    Darabi, A.; Wyagnanski, I.
  • Computational Methods for Fluid Dynamics
    Ferziger, H.J.; Peric, M.
  • FLUENT Version 6.2 User Manual
    FLUENT
  • Modern developments in flow control
    Gad‐el‐Hak, M.
  • Flow Control Passive, Active, and Reactive Flow Management
    Gad‐el‐Hak, M.
  • The control of flow separation by periodic excitation
    Greenblatt, D.; Wygnanski, I.
  • Effect of leading‐edge curvature on airfoil separation control
    Greenblatt, D.; Wygnanski, I.
  • Two‐dimensional turbulent viscous flow simulation past airfoils at fixed incidence
    Guilmineau, E.; Piquet, J.; Queutey, P.
  • Separation control using moving surface effects: a numerical simulation
    Hassan, A.A.; Sankar, L.N.
  • Suppression of vortex shedding for flow around a circular cylinder using optimal control
    Homescu, C.; Navon, I.M.; Li, Z.
  • Numerical study of blowing and suction mechanism on NACA 0012 airfoil
    Huang, L.; Huang, P.G.; LeBeau, R.P.
  • Optimization of blowing and suction control on NACA 0012 airfoil using genetic algorithm
    Huang, L.; LeBeau, R.P.; Huang, P.G.; Hauser, Th.
  • Vortex‐generator model and its application to flow control
    Jirásek, A.
  • The prediction of laminarization with a two‐equation model of turbulence
    Jones, W.P.; Launder, B.E.
  • Simple high‐accuracy resolution program for convective modeling of discontinuities
    Leonard, B.P.
  • Separation control from the flap of a high lift airfoil using DBD plasma actuators
    Little, J.; Nishihara, M.; Adamovich, I.; Samimy, M.
  • Optimal and robust control of fluid flows: some theoretical and computational aspects
    Medjo, T.T.; Temam, R.; Ziane, M.
  • Two‐equation eddy‐viscosity turbulence models for engineering applications
    Menter, F.R.
  • Ten years of industrial experience with the SST turbulence model
    Menter, F.R.; Kuntz, M.; Langtry, R.
  • Simulation and optimization of flow control strategies for novel high‐lift configurations
    Meunier, M.
  • Moving surface boundary layer control: a review
    Modi, V.J.
  • Effect of moving surface on the airfoil boundary‐layer control
    Modi, V.J.; Mokhtarian, F.
  • Fluid dynamics of airfoils with moving surface boundary layer control
    Mokhtarian, F.; Modi, V.J.
  • An active flow control strategy for the suppression of vortex structures behind a circular cylinder
    Muddada, S.; Patnaik, B.S.V.
  • An artificial compressibility based characteristic based split (CBS) scheme for steady and unsteady turbulent incompressible flows
    Nithiarasu, P.; Liu, C.B.
  • Controlling chaos
    Ott, E.; Grebogi, C.; Yorke, J.A.
  • Numerical Heat Transfer and Fluid Flow
    Patankar, S.V.
  • Controlling wake turbulence
    Patnaik, B.S.V.P.; Wei, G.W.
  • Simulation of laminar confined flow past a circular cylinder with integral wake splitter involving heat transfer
    Patnaik, B.S.V.P.; Seetharamu, K.N.; Narayana, P.A.A.
  • Comparison of LES and RANS calculation of the flow around bluff bodies
    Rodi, W.
  • Delay of airfoil stall by periodic excitation
    Seifert, A.; Darabi, A.; Wygnanski, I.
  • Flow control for the systematic buildup of high‐lift systems
    Shmilovich, A.; Yadlin, Y.
  • Active flow control for practical high‐lift systems
    Shmilovich, A.; Yadlin, Y.
  • Problems with leading‐edge flow control experiments
    Sunneechurra, K.; Crowther, W.
  • Controlling flow turbulence with moving controllers
    Tang, G.; Guan, S.; Hu, G.
  • Influences of element size and variable smoothing on inviscid compressible flow solution
    Thomas, C.; Nithiarasu, P.
  • Aircraft viscous drag reduction using riblets
    Viswanath, P.R.
  • Some thoughts on separation control strategies
    Viswanath, P.R.
  • Synchronization of single‐side locally averaged adaptive coupling and its application to shock capturing
    Wei, G.W.
  • Active control of flow separation over an airfoil using synthetic jets
    You, D.; Moin, P.