Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing PDF Download
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Author: Arvid L. Keith
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
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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.
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
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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 [degrees] Sweptback Wing PDF](https://books.google.com/books/content/images/frontcover/WBXTtgAACAAJ?fife=w80-h100)
Author: Arvid L. Keith
Publisher:
ISBN:
Category :
Languages : en
Pages : 63
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Book Description
Author: Arvid L. Keith
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 65
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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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
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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.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
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Book Description
Author: Harold S. Johnson
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Book Description
Author: James A. Weilberg
Publisher:
ISBN:
Category :
Languages : en
Pages : 64
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Book Description
Author: Beverly Z. Jr Henry
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: Robert E. Dannenberg
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 678
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Book Description
Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
