Investigation of Leading-edge Blowing on a Thin Airfoil PDF Download
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Author: Gustave W. Schwartz
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Author: Gustave W. Schwartz
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Author: Jules B. Dods (Jr.)
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 145
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The investigation reported herein consists of three phases: (1) an experimental investigation of a thin airfoil with blowing over a trailing-edge flap; (2) a comparison of the results of the experimental investigation with the results of other similar investigations; and (3) a theoretical study of the relationships among the air-flow and power parameters for the general blowing case.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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Author:
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ISBN:
Category :
Languages : en
Pages : 64
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Author: B.G. McLachlan
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
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Author: Israel Wygnanski
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Category :
Languages : en
Pages :
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"Experiments have been made on a thin, two-dimensional aerofoil with sharp leading edge and with a jet blowing through a mid-chord slot on the upper surface for boundary-layer and circulation control.The measurements were made at low Mach number and included the effect of altering the angle of blowing for it was anticipated that this would help control the leading edge separation bubble.It was found that variation of the blowing angle caused very little change in lift coefficient but produced an appreciable change in moment coefficient. With the jet discharging at an angle and subsequently reattaching to the surface a separation bubble of low pressure was formed downstream of the slot which reduced the nose-up pitching moment about the guarter-chord point. The reattachment distances for this bubble have been successfully predicted by an extension of the Bourque-Newman theory for reattaching jets. The lift and moment coefficients before the stall were compared with Spence's jet flap theory which has been extended within the context of thin aerofoil theory, to include the effect of jet entrainment. It is predicted that the entrainment tends to increase the lift by increasing the effective camber of the aerofoil and the detailed agreement between this theory and experiment is good." --
Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 57
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Book Description
An investigation has been conducted in the Langley full-scale tunnel to determine the effects on the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. The wing and horizontal tail have an aspect ratio of 3.5, taper ratio of 0.3, leading-edge sweep of 49 degrees, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The trailing-edge air was ejected over highly deflected half- and full-span flaps in combination with several leading-edge-flow control devices including blowing from a slot in the wing leading edge. The momentum coefficient range was investigated was 0 to 0.16 for the trailing-edge blowing and 0 to 0.025 for the leading-edge blowing. Most of the tests were conducted at a Reynolds number of 5,200,000 corresponding to a Mach number of 0.08.
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Author: Timothy Wang
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 312
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Author: Richard L. Perry (CAPT, USAF.)
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 150
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