Author: Gustave W. Schwartz
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Investigation of Leading-edge Blowing on a Thin Airfoil
Author: Gustave W. Schwartz
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
The Effects of Blowing Over Various Trailing-edge Flaps on an NACA 0006 Airfoil Section, Comparisons with Various Types of Flaps on Other Airfoil Sections, and an Analysis of Flow and Power Relationships for Blowing Systems
Author: Jules B. Dods (Jr.)
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 145
Book Description
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.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 145
Book Description
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.
A PRELIMINARY INVESTIGATION OF THE EFFECT OF A BLOWING SLOT NEAR THE LEADING EDGE OF AN AIRFOIL.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
Book Description
Low-Speed Investigation of Upper-Surface Leading-Edge Blowing on a High-Speed Civil Transport Configuration
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 64
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 64
Book Description
A Study of a Circulation Control Airfoil with Leading/trailing Edge Blowing
Author: B.G. McLachlan
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
Book Description
Theoretical and Experimental Investigation of Blowing Applied to an Aerofoil with a Sharp Leading Edge
Author: Israel Wygnanski
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
"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." --
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
"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." --
Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-body-tail Configuration in Combination with Leading-edge Devices
Author: H. Clyde McLemore
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 57
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.
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 57
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.
Low-speed Experimental Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose and Trailing-edge Flaps
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Book Description
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.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Book Description
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.
An Experimental Study of the Effects of Leading-edge Blowing Upon the Characteristics of a Jet-flapped Airfoil
Author: Timothy Wang
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 312
Book Description
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 312
Book Description
An Experimental Investigation of the Aerodynamic Characteristics of a Thin Supercritical Airfoil with Small Leading Edge Radius
Author: Richard L. Perry (CAPT, USAF.)
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 150
Book Description
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 150
Book Description