Author: Arvid L. Keith
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
Low-Speed Wind-Tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Deg Sweptback Wing
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 deg mounted in the mid-wing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 deg mounted in the mid-wing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 65
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 65
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 [degrees] Sweptback Wing
Author: Arvid L. Keith
Publisher:
ISBN:
Category :
Languages : en
Pages : 63
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 63
Book Description
Research Abstracts
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
Book Description
Research Abstracts and Reclassification Notice
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Transonic Wind-tunnel Investigation of the Interference Between a 45© Sweptback Wing and a Systematic Series of Four Bodies
Author: Donald L. Loving
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
Book Description
Wind-tunnel Investigation at Low Speed of the Effect of Varying the Ratio of Body Diameter to Wing Span from 0.1 to 0.8 on the Aerodynamic Characteristics in Pitch of the 45© Sweptback-wing--body Combination
Author: Harold S. Johnson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Book Description
Low-speed Wind-tunnel Investigation of Jet Control on a 35© Swept Wing
Author: John G. Lowry
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Wind Tunnel Investigation at Low Speed of the Effect of Varying the Ratio of Body Diameter to Wing Span from 0.1 to 0.8 on the Aerodynamic Characteristics in Pitch of a 45 Degree Sweptback-wing-body Combination
Author: Harold S. Johnson
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description