Wind-tunnel Investigation at Supersonic Speeds of a Canard-controlled Missile with Fixed and Free-rolling Tail Fins PDF Download
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Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 84
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Book Description
Author: A. B. Blair
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 84
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author: A.B. Jr Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
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Book Description
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.
Author: Jerry M. Allen
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 64
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Book Description
Abstract: A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.60, 1.90, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple one-axis canard controller. This concept, which features and axisymmetric body with two planar canards and four wraparound tail fins arranged in opposing pairs, must be in rolling motion to be controllable in any radial plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide the motion is desirable. Two tail-fin shaping designs, one shaved and one beveled, were evaluated for their efficiency in producing the needed rolling moments, and the results showed that the shaved fins were much more desirable for this task than the beveled fins.
Author: A. B. Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 106
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 86
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 802
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Book Description
Author: James DeSpirito
Publisher:
ISBN: 9781423506669
Category :
Languages : en
Pages : 91
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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.
