Read Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins

Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins

James DeSpirito

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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.We have made it easy for you to find a PDF Ebooks without any digging. And by having access to our ebooks online or by storing it on your computer, you have convenient answers with Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins. To get started finding Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins, you are right to find our website which has a comprehensive collection of manuals listed.
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Pages: 212

Format: PDF, EPUB & Kindle Edition

Publisher: —

Release: 2004

ISBN: oOgJmY8JmUYC

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.We have made it easy for you to find a PDF Ebooks without any digging. And by having access to our ebooks online or by storing it on your computer, you have convenient answers with Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins. To get started finding Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins, you are right to find our website which has a comprehensive collection of manuals listed.
Our library is the biggest of these that have literally hundreds of thousands of different products represented.

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Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins

Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins

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