Low-speed Lateral-control Investigation of a Flap-type Spoiler Aileron with and Without a Deflector and Slot on a 6-percent-thick, Tapered, 45 Degree Sweptback Wing of Aspect Ratio 4 PDF Download
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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: 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: Alexander D. Hammond
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 21
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Book Description
An investigation has been made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap extending from the 14- to the 67-percent-semispan station. The wing has a sweepback of 45 degree of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil parallel to the plane of symmetry. Additional tests were made with the flap neutral to evaluate the effects of deflector projection on the characteristics of the wing equipped with a spoiler-slot-deflector configuration having the same span and spanwise position as the spoiler and deflector had with the flap deflected.
Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 25
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Book Description
A wind-tunnel investigation has been made at low speed in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of deflector projection on the control effectiveness of spoiler-slot-deflectors on a 30 degree sweptback wing-fuselage model equipped with either a 15-percent-chord spoiler or a spoiler-slot-deflector that extended from the 20- to the 99-percent-semispan station of the right ring. The wing had an aspect ratio of 3, a taper ratio of 0.5, and NACA 65A004 airfoil section. The tests were made at angles of attack from -4 to 24 degrees at Mach number of 0.26 for control projections from 0 to 12 percent chord. The deflector of the spoiler-slot-deflector configuration was tested at projections from zero to a projection equal to the spoiler projection at each spoiler projection.
Author: Powell M. Lovell
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 30
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Book Description
A free-flight-tunnel investigation has been made to compare the dynamic lateral control characteristics provided by step plug ailerons on a sweptback-wing model having full-span flaps. The model had a 38 degree sweptback wing with an aspect ratio of 3 and a taper ratio of 0.05. The static stability and control characteristics of the flight-test model were determined from force tests and the time-lag characteristics of the ailerons were determined from stand tests in which there was freedom only in roll. Flight tests of the model were made over a range of lift coefficient from 1.0 through the stall.
Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 25
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Book Description
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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Book Description
This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
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: Alexander D. Hammond
Publisher:
ISBN:
Category :
Languages : en
Pages : 19
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Book Description
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: Alexander D. Hammond
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 21
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Book Description
