Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers PDF Download

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Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers

Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers PDF Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92

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Book Description

Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers

Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers PDF Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92

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Book Description

Effect of Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers

Effect of Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers PDF Author: A. B. Jr Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 92

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Book Description

NASA Technical Paper

NASA Technical Paper PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 134

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Book Description

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 PDF Author: James DeSpirito
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 212

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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.

Sideslip Characteristics at Various Angles of Attack for Several Hypersonic Missile Configurations with Canard Controls at a Mach Number of 2.01

Sideslip Characteristics at Various Angles of Attack for Several Hypersonic Missile Configurations with Canard Controls at a Mach Number of 2.01 PDF Author: Gerald V. Foster
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30

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Book Description

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails PDF Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44

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Book Description

Longitudinal Stability and Control Characteristics from a Flight Investigation of a Cruciform Canard Missile Configuration Having an Exposed Wing-canard Area Ratio of 16:1

Longitudinal Stability and Control Characteristics from a Flight Investigation of a Cruciform Canard Missile Configuration Having an Exposed Wing-canard Area Ratio of 16:1 PDF Author: Martin T. Moul
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 42

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Book Description

Vortex Flows at Supersonic Speeds

Vortex Flows at Supersonic Speeds PDF Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 104

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Book Description

Wind-tunnel Investigation at Supersonic Speeds of a Canard-controlled Missile with Fixed and Free-rolling Tail Fins

Wind-tunnel Investigation at Supersonic Speeds of a Canard-controlled Missile with Fixed and Free-rolling Tail Fins PDF Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 84

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Book Description

Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Maneuverable Missile with In-line Cruciform Wings and Canard Surfaces

Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Maneuverable Missile with In-line Cruciform Wings and Canard Surfaces PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 52

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Book Description
An investigation has been conducted in the Langley Unitary Plan wind tunnel at Mach numbers from 1.50 to 4.63 to determine the aerodynamic characteristics of a maneuverable missile having in-line cruciform wings and canard surfaces oriented in 45° roll planes.