The Effects of Leading Edge Suction on Delta Wing Vortex Breakdown PDF Download
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Author: Brant H. Maines
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Brant H. Maines
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: H. Q. Yang
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Scott Duncan McCormick
Publisher:
ISBN:
Category :
Languages : en
Pages : 114
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Book Description
Author: Edward C. Polhamus
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ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 18
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Book Description
Author: Ian Kenneth Maynard
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ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 150
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Author: X. Z. Huang
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Category :
Languages : en
Pages :
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Author: Ismet Gursul
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ISBN:
Category : Leading edges (Aerodynamics)
Languages : en
Pages : 60
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Book Description
Several control techniques have been applied in order to control leading-edge vortices at high angle of attack. The purpose of these control techniques is to influence the strength and structure of the vortices, to generate rolling moment, and to delay vortex breakdown. Since the vorticity of the leading-edge vortices originates from the separation point along the leading-edge, control of development of the shear layer has been chosen as a control strategy in several investigations: blowing and suction in the tangential direction along a rounded leading-edge.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Author: Edward Charles Polhamus
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Category : Aerodynamics
Languages : en
Pages : 28
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Book Description
A concept for the calculation of the vortex lift of sharp-edge delta wings is presented and compared with experimental data. The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading-edge. This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack 20[degrees] or greater.
Author: Anthony M. Mitchell
Publisher:
ISBN: 9781423535225
Category :
Languages : en
Pages : 380
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Book Description
Demands for more maneuverable and stealthy air vehicles have encouraged the development of new control concepts for separated flows. The goalof this research is the control of leading-edge vortex breakdown by open-loop, along-the-core blowing near the apex of a delta wing to improve lift and maneuverability at high angles of attack. Control is dependent on the knowledge of and the ability to detect principle characteristics of the phenomena. Therefore, an experimental study of a 700 delta wing was accomplished to better understand the physical properties of the vortical flow and the vortex breakdownphenomena. Multiple experimental methods were used to characterize the flow field and its influence on the model's surfaces as well as to identify parameters for closed-loop feedback control.
