Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins PDF full book. Access full book title Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins by James DeSpirito. Download full books in PDF and EPUB format.
Author: James DeSpirito
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 212
Get Book Here
Book Description
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.
Author: James DeSpirito
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 212
Get Book Here
Book Description
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.
Author: James DeSpirito
Publisher:
ISBN: 9781423515555
Category :
Languages : en
Pages : 104
Get Book Here
Book Description
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.
Author: James DeSpirito
Publisher:
ISBN: 9781423506669
Category :
Languages : en
Pages : 91
Get Book Here
Book Description
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 91
Get Book Here
Book Description
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 104
Get Book Here
Book Description
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.
Author: James DeSpirito
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 79
Get Book Here
Book Description
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.
Author: S. Kishore Kumar
Publisher: Springer Nature
ISBN: 9811596018
Category : Technology & Engineering
Languages : en
Pages : 529
Get Book Here
Book Description
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.
Author: A. B. Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 106
Get Book Here
Book Description
Author: James DeSpirito
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 84
Get Book Here
Book Description
