High-speed Wind-tunnel Investigation of Sweptback Wing with an Added Triangular Area at the Center PDF Download
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Author: Beverly Z. Jr Henry
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Beverly Z. Jr Henry
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Macon C. Ellis
Publisher:
ISBN:
Category : Aerodynamic, Supersonic
Languages : en
Pages : 44
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Book Description
Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1268
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
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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: Russell W. McDearmon
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 42
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Experimental values of the damping in roll of three triangular wings have been obtained at Mach numbers of 1.62, 1.94, 2.22, 2.41, and 2.62 over a range of angle of attack from approximately 0 to 13 degrees. The aspect ratios of the wings were 1.46, 2.31, and 3.35.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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Author: Donald L. Loving
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 52
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Author: John G. Lowry
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
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![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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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
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