Leading Edge Vortex-flap Experiments on a 74 Deg. Delta Wing PDF Download
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Author: Dhanvada M. Rao
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 12
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Book Description
Exploratory wind-tunnel tests are reported on a 74 deg. delta wing model to evaluate the potential of a vortex-flap concept in reducing the subsonic lift-dependent drag of highly swept, slender wings. The concept utiliizes the suction effect of coiled vortices generated through controlled separation over leading-edge flap surfaces to produce a thrust component. A series of vortex-flap configurations were investigated to explore the effect of some primary geometric variables. The most promising flap arrangement produced drag reductions in excess of 30% relative to the basic wing in the range of lift coefficient 0.4 to 0.8.
Author: Dhanvada M. Rao
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 12
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Book Description
Exploratory wind-tunnel tests are reported on a 74 deg. delta wing model to evaluate the potential of a vortex-flap concept in reducing the subsonic lift-dependent drag of highly swept, slender wings. The concept utiliizes the suction effect of coiled vortices generated through controlled separation over leading-edge flap surfaces to produce a thrust component. A series of vortex-flap configurations were investigated to explore the effect of some primary geometric variables. The most promising flap arrangement produced drag reductions in excess of 30% relative to the basic wing in the range of lift coefficient 0.4 to 0.8.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
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Author: Arthur C. Grantz
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 152
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Book Description
The low speed lateral/directional characteristics of a generic 74 degree delta wing body configuration employing the latest generation, gothic planform vortex flaps was determined. Longitudinal effects are also presented. The data are compared with theoretical estimates from VORSTAB, an extension of the Quasi vortex lattice Method of Lan which empirically accounts for vortex breakdown effects in the calculation of longitudinal and lateral/directional aerodynamic characteristics. It is indicated that leading edge deflections of 30 and 40 degrees reduce the magnitude of the wing effective dihedral relative to the baseline for a specified angle of attack or lift coefficient. For angles of attack greater than 15 degrees, these flap deflections reduce the configuration directional stability despite improved vertical tail effectiveness. It is shown that asymmetric leading edge deflections are inferior to conventional ailerons in generating rolling moments. VORSTAB calculations provide coarse lateral/directional estimates at low to moderate angles of attack. The theory does not account for vortex flow induced, vertical tail effects.
Author: Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
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Author: Daniel Francis Hunter
Publisher:
ISBN:
Category :
Languages : en
Pages : 428
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Author: Gary T. Chapman
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 46
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Author: Sejong Oh
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 162
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Author: Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 17
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