Investigation of Flap-type Ailerons on an Untapered Wing Having an Aspect Ratio of 3.7, 45 Degree Sweepback, and an NACA 65A009 Airfoil Section PDF Download
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Author: Richard G. MacLeod
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 18
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Book Description
An investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model was made in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream. Rolling moments were obtained through a small range of angles of attack and aileron deflections. Lift data on the complete model are also included.
Author: Richard G. MacLeod
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 18
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Book Description
An investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model was made in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream. Rolling moments were obtained through a small range of angles of attack and aileron deflections. Lift data on the complete model are also included.
Author: James M. Watson
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 11
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Book Description
An investigation has been made in the Langley 300 MPH 7- by 10-foot tunnel to determine the lateral control characteristics of a deflector and slot arrangement in conjunction with a flap-type spoiler aileron. The wing had a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free air stream.
Author: Jack Fischel
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 44
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Book Description
Results and discussion are presented of a low-speed lateral-control investigation of three untapered unswept wings of aspect ratio 1.13, 2.13, and 4.13 and an untapered 45 degrees sweptback wing of aspect ratio 2.09 equipped with 0.60-semispan retractable ailerons having various projections. Continuous-span ailerons were tested at outboard stations on the unswept wings, and plain (continuous span) and stepped (segmented) ailerons were tested at various spanwise stations with and without simulated actuating arms on the sweptback wing.
Author: John R. Hagerman
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 40
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Book Description
A low-speed wind-tunnel investigation was made to determine the lateral control characteristics of extensible wing-tip ailerons on an untapered semispan wing having two configurations; one configuration was unswept and had an aspect ratio of 3.13 and the other configuration was swept back 45 degrees and had an aspect ratio of 1.59. Three plan forms of extensible ailerons were investigated on each wing configuration at various amounts of extension and deflection relative to the wing-chord plane. Also, wing aerodynamic characteristics were determined for the two plain-wing configurations.
Author: Harold S. Johnson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 38
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Book Description
A wind-tunnel investigation at low speed was made to determine the lateral control characteristics of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain unsealed ailerons. Variations of the lateral-control data with aileron span and spanwise location were determined through a large aileron-deflection range for various angles of attack up to about the angle of maximum lift.
Author: Raymond D. Vogler
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 21
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Book Description
As part of an NACA search program, an investigation by the transonic-bump method through a Mach range of 0.7 to 1.15 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Author: F. E. West
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 59
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Book Description
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the characteristics of several flap-type spoiler ailerons, lower-surface deflector ailerons, and spoiler-slot-deflector ailerons. These controls were located in the vicinity of the 70-percent wing chord line and extended outboard to 87 percent of the wing semispan. The flap-type spoilers were tested at only one projection. The wing of the wing-body combination used in these tests had 45 degree sweepback, an aspect ratio of 4.0, a taper ratio of 0.60, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Six-component force and moment data were obtained at Mach numbers from 0.60 to 1.03 (Reynolds numbers from 5,050,000 to 6,000,000) for an angle-of-attack range from 0 to approximately 20 degrees.
Author: Rodger L. Naeseth
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 44
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Book Description
A low-speed wind-tunnel investigation was made to determine the static lateral control characteristics of flap-type and retractable spoiler-type ailerons on a rigid sweptback wing, a flexible sweptback wing, and a flexible M-wing. A few tests were also made with a half-delta tip control on the flexible sweptback wing. The semispan wing models were of aspect ratio 6.0, taper ratio of 0.6, and had NACA 65A009 airfoil sections parallel to the free-stream direction. The quarter-chord lines of the wings were swept 45 degrees and the break in the M-wing was at the half semispan location.
Author: Homer B. Wilson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 89
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Book Description
This paper presents effects of the deflection of a flat-type aileron on the chordwise pressure distribution at the 46-percent-semispan station of a tapered 35 degree sweptback wing of aspect ratio 4 with an NACA 65A006 airfoil section. The tests were made at angles of attack from 0 to 20 degrees and at Mach numbers from 0.60 to 0.95 for aileron deflections from -30 to 30 degrees.
Author: George W. Jones
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
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Book Description
A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.
