Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins
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Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins
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Author : James DeSpirito
language : en
Publisher:
Release Date : 2004
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins written by James DeSpirito and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004 with Computational fluid dynamics categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part 1 Supersonic Flow
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Author :
language : en
Publisher:
Release Date : 2002
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part 1 Supersonic Flow written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flowfield around a generic canard-controlled missile configuration in supersonic flow. Computations were performed for Mach 1.5 and 3.0, at six angles of attack between 0 and 10, with 0 and 10 canard deflection, and with planar and grid tail fins, for a total of 48 cases. Validation of the computed results was demonstrated by the very good agreement between the computed aerodynamic coefficients and those obtained from wind tunnel measurements. Visualizations of the flowfield showed that the canard trailing vortices and downwash produced a low-pressure region on the starboard side of the missile that in turn produced an adverse side force. The pressure differential on the leeward fin produced by the interaction with the canard trailing vortices is primarily responsible for the adverse roll effect observed when planar fins are used. Grid tail fins improved the roll effectiveness of the canards at low supersonic speed. No adverse rolling moment was observed with no canard deflection, or at the higher supersonic speed for either tail fin type due to the lower intensity of the canard trailing vortices in these cases. Flow visualizations from the simulations performed in this study help in the understanding of the flow physics and can lead to improved canard and tail fin designs for missiles and rockets.
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins
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Author : James DeSpirito
language : en
Publisher:
Release Date : 2004-03
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins written by James DeSpirito and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004-03 with categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha > 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part 1 Supersonic Flow
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Author : James DeSpirito
language : en
Publisher:
Release Date : 2002-09
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part 1 Supersonic Flow written by James DeSpirito and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002-09 with categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flowfield around a generic canard-controlled missile configuration in supersonic flow. Computations were performed for Mach 1.5 and 3.0, at six angles of attack between 0 and 10, with 0 and 10 canard deflection, and with planar and grid tail fins, for a total of 48 cases. Validation of the computed results was demonstrated by the very good agreement between the computed aerodynamic coefficients and those obtained from wind tunnel measurements. Visualizations of the flowfield showed that the canard trailing vortices and downwash produced a low-pressure region on the starboard side of the missile that in turn produced an adverse side force. The pressure differential on the leeward fin produced by the interaction with the canard trailing vortices is primarily responsible for the adverse roll effect observed when planar fins are used. Grid tail fins improved the roll effectiveness of the canards at low supersonic speed. No adverse rolling moment was observed with no canard deflection, or at the higher supersonic speed for either tail fin type due to the lower intensity of the canard trailing vortices in these cases. Flow visualizations from the simulations performed in this study help in the understanding of the flow physics and can lead to improved canard and tail fin designs for missiles and rockets.
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part Ii Subsonic And Transonic Flow
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Author :
language : en
Publisher:
Release Date : 2004
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins Part Ii Subsonic And Transonic Flow written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004 with categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins
DOWNLOAD
Author : James DeSpirito
language : en
Publisher:
Release Date : 2002
Numerical Investigation Of Aerodynamics Of Canard Controlled Missile Using Planar And Grid Tail Fins written by James DeSpirito and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with Computational fluid dynamics categories.
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flowfield around a generic canard-controlled missile configuration in supersonic flow. Computations were performed for Mach 1.5 and 3.0, at six angles of attack between 0 and 10, with 0 and 10 canard deflection, and with planar and grid tail fins, for a total of 48 cases. Validation of the computed results was demonstrated by the very good agreement between the computed aerodynamic coefficients and those obtained from wind tunnel measurements. Visualizations of the flowfield showed that the canard trailing vortices and downwash produced a low-pressure region on the starboard side of the missile that in turn produced an adverse side force. The pressure differential on the leeward fin produced by the interaction with the canard trailing vortices is primarily responsible for the adverse roll effect observed when planar fins are used. Grid tail fins improved the roll effectiveness of the canards at low supersonic speed. No adverse rolling moment was observed with no canard deflection, or at the higher supersonic speed for either tail fin type due to the lower intensity of the canard trailing vortices in these cases. Flow visualizations from the simulations performed in this study help in the understanding of the flow physics and can lead to improved canard and tail fin designs for missiles and rockets.
Design And Development Of Aerospace Vehicles And Propulsion Systems
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Author : S. Kishore Kumar
language : en
Publisher: Springer Nature
Release Date : 2021-03-18
Design And Development Of Aerospace Vehicles And Propulsion Systems written by S. Kishore Kumar and has been published by Springer Nature this book supported file pdf, txt, epub, kindle and other format this book has been release on 2021-03-18 with Technology & Engineering categories.
This book presents selected papers presented in the Symposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD 2018), which was jointly organized by Aeronautical Development Agency (the nodal agency for the design and development of combat aircraft in India), Gas-Turbine Research Establishment (responsible for design and development of gas turbine engines for military applications), and CSIR-National Aerospace Laboratories (involved in major aerospace programs in the country such as SARAS program, LCA, Space Launch Vehicles, Missiles and UAVs). It brings together experiences of aerodynamicists in India as well as abroad in Aerospace Vehicle Design, Gas Turbine Engines, Missiles and related areas. It is a useful volume for researchers, professionals and students interested in diversified areas of aerospace engineering.
Wind Tunnel Investigation At Mach Numbers From 1 90 To 2 86 Of A Canard Controlled Missile With Ram Air Jet Spoiler Roll Control
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Author : A. B. Blair
language : en
Publisher:
Release Date : 1978
Wind Tunnel Investigation At Mach Numbers From 1 90 To 2 86 Of A Canard Controlled Missile With Ram Air Jet Spoiler Roll Control written by A. B. Blair and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with categories.
Subsonic Flow Cfd Investigation Of Canard Controlled Missile With Planar And Grid Fins
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Author : James DeSpirito
language : en
Publisher:
Release Date : 2003
Subsonic Flow Cfd Investigation Of Canard Controlled Missile With Planar And Grid Fins written by James DeSpirito 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.
Wind Tunnel Investigation At Supersonic Speeds Of A Canard Controlled Missile With Fixed And Free Rolling Tail Fins
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Author : A. B. Blair
language : en
Publisher:
Release Date : 1978
Wind Tunnel Investigation At Supersonic Speeds Of A Canard Controlled Missile With Fixed And Free Rolling Tail Fins written by A. B. Blair and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1978 with Aerodynamics, Supersonic categories.