Flow Control Of A Naca 0015 Airfoil Using A Chordwise Array Of Synthetic Jets

DOWNLOAD

Download Flow Control Of A Naca 0015 Airfoil Using A Chordwise Array Of Synthetic Jets PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Flow Control Of A Naca 0015 Airfoil Using A Chordwise Array Of Synthetic Jets book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page

Flow Control Of A Naca 0015 Airfoil Using A Chordwise Array Of Synthetic Jets

DOWNLOAD
Author : Kevin Bales
language : en
Publisher:
Release Date : 2003

Flow Control Of A Naca 0015 Airfoil Using A Chordwise Array Of Synthetic Jets written by Kevin Bales and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with categories.

Iutam Symposium On Flow Control And Mems

DOWNLOAD
Author : Jonathan F. Morrison
language : en
Publisher: Springer Science & Business Media
Release Date : 2010-09-09

Iutam Symposium On Flow Control And Mems written by Jonathan F. Morrison and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2010-09-09 with Technology & Engineering categories.

The Symposium brought together many of the world’s experts in fluid mechanics, microfabrication and control theory to discover the synergy that can lead to real advances and perhaps find ways in which collaborative projects may proceed. The high profile meeting was attended by keynote speakers who are leaders in their fields. A key driver was the improvement in flow efficiency to reduce drag, and thereby emissions arising from transport. About 65 papers were presented.

41st Aiaa Aerospace Sciences Meeting Exhibit

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 2003

41st Aiaa Aerospace Sciences Meeting Exhibit written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with Aeronautics categories.

Active Flow Control Over A Naca 0015 Airfoil By Synthetic Jet Actuators

DOWNLOAD
Author : Pooya Kabiri
language : en
Publisher:
Release Date : 2012

Active Flow Control Over A Naca 0015 Airfoil By Synthetic Jet Actuators written by Pooya Kabiri and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012 with Aerodynamics categories.

Flow Control On A Naca 4418 Airfoil Using Streamwise Synthetic Jet Actuators

DOWNLOAD
Author : Yves Daniel Loretz
language : en
Publisher:
Release Date : 2001

Flow Control On A Naca 4418 Airfoil Using Streamwise Synthetic Jet Actuators written by Yves Daniel Loretz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with Jets categories.

Hingeless Flow Control Over An Airfoil Via Distributed Actuation

DOWNLOAD
Author : Anmol Agrawal
language : en
Publisher:
Release Date : 2007

Hingeless Flow Control Over An Airfoil Via Distributed Actuation written by Anmol Agrawal and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2007 with categories.

An experimental investigation was undertaken to test the effectiveness of a novel design for controlling the aerodynamics of an airfoil. A synthetic jet actuator (SJA) was placed inside a NACA 0015 airfoil with its jet at 12.5% of the chord length, hereby referred to as the leading edge actuator. Four centrifugal fans across the span were mounted at 70%of the chord and the jet formed by them was located at 99% of the chord, hereby referred to as the trailing edge actuator. The effects of these actuators on the aerodynamic properties were studied, separately and then in conjunction, with varying angles of attack. The leading edge actuator delays the onset of stall up to 24 degrees, the maximum angle of attack that could be attained. The control of the aerodynamics was achieved by controlling the amount of separated region. There was no effect of the actuation at lower angles of attack. The trailing edge actuator provides aerodynamic control at both low and high angles of attack. The study investigated the effect of jet momentum coefficient on the aerodynamic properties for various angles of attack. The data obtained shows that lift control (in both positive and negative direction) was achieved even at low angles. The actuator enhances the aerodynamic properties by changing the pressure distribution as well as by delaying flow separation. Study of the combined actuation shows that the synthetic jet actuator was very effective in delaying stall when the trailing edge jet was ejected from the upper surface. For the case when the jet is ejected from the lower surface, there is less control. This can be accounted for by the difference in aerodynamic loading for both cases.

Hingeless Flow Control Over An Airfoil

DOWNLOAD
Author : Anmol Agrawal
language : en
Publisher: LAP Lambert Academic Publishing
Release Date : 2011-07

Hingeless Flow Control Over An Airfoil written by Anmol Agrawal and has been published by LAP Lambert Academic Publishing this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-07 with categories.

An experimental investigation was undertaken to test the effectiveness of a novel design for controlling the aerodynamics of an airfoil. A synthetic jet actuator (SJA) was placed inside a NACA 0015 airfoil with its jet at 12.5% of the chord length, hereby referred to as the leading edge actuator. Four centrifugal fans across the span were mounted at 70% of the chord and the jet formed by them was located at 99% of the chord, hereby referred to as the trailing edge actuator. The effects of these actuators on the aerodynamic properties were studied, separately and then in conjunction, with varying angles of attack. The leading edge actuator delays the onset of stall up to 24 degrees, the maximum angle of attack that could be attained. The control of the aerodynamics was achieved by controlling the amount of separated region. There was no effect of the actuation at lower angles of attack. The trailing edge actuator provides aerodynamic control at both low and high angles of attack. The study investigated the effect of jet momentum coefficient on the aerodynamic properties for various angles of attack.

Active Flow Control Of A Two Dimensional Naca 0036 Airfoil With Synthetic Jet Excitations

DOWNLOAD
Author : Jacob Wilson
language : en
Publisher:
Release Date : 2005

Active Flow Control Of A Two Dimensional Naca 0036 Airfoil With Synthetic Jet Excitations written by Jacob Wilson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2005 with Aerofoils categories.

An active flow control experiment was conducted on a 2-ft chord NACA 0036 airfoil at 10 degrees angle of attack in the Cal Poly 3' x 4' wind tunnel.

Numerical Study On Active Flow Control Using Synthetic Jet Actuators Over A Naca 4421 Airfoil

DOWNLOAD
Author : Xavier Guerrero Pich
language : en
Publisher:
Release Date : 2015

Numerical Study On Active Flow Control Using Synthetic Jet Actuators Over A Naca 4421 Airfoil written by Xavier Guerrero Pich and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015 with categories.

This study is focused on evaluating the effects of using a Zero Net Mass Flux (ZNMF) actuator on a NACA 4421 airfoil for active flow control. First part of the study presents the fundamentals of boundary layer and a study of the available devices which are more used for flow control, focusing on the ZNMF. The steps for creating the mesh to perform numerical simulations of the airfoil are explained, and the results of the CFD simulations are compared with experimental data as a vaseline balidation. In the secord part, the ZNMF is studied in order to set the parameters of the actuator and to simulate its effect on CFD, and moreover the numerical simulations of the airfoil with the ZNMF set up are performed and the results are evaluated. The evaluation will show the most optimum parameters for the actuator, as well as the effects that the ZNMF has on the airfoil's behaviour.

Investigation Of Flow Over Naca 0015 Airfoil With Trailing Edge Jet

DOWNLOAD
Author : Nora Anyango Okong'o
language : en
Publisher:
Release Date : 1993

Investigation Of Flow Over Naca 0015 Airfoil With Trailing Edge Jet written by Nora Anyango Okong'o and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with categories.