Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps PDF Download
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Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Book Description
Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Book Description
Author: Roy H. Lange
Publisher:
ISBN:
Category :
Languages : en
Pages : 57
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Book Description
Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 88
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Book Description
Author: Stanley H. Spooner
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
Author: Mitchel H. Bertram
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 134
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Author: Edward C. B. Danforth
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
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Book Description
Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Author: James W. Schmeer
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
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An investigation was conducted in the Langley 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped 6 degrees about the 19-percent chord line from 0.15 semispan to the wing tip. Data were obtained at Mach numbers of 0.80 to 1.03 with average Reynolds numbers of 5,700,000 to 6,300,000, respectively. The results of this investigation are compared with the pressure data obtained with the undrooped or basic wing of a previous investigation.
Author:
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ISBN:
Category :
Languages : en
Pages : 25
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Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Author: Robert L. Woods
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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