Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section PDF full book. Access full book title Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by Robert F. Thompson. Download full books in PDF and EPUB format.
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Get Book Here
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: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Get Book Here
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: Raymond D. Vogler
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 21
Get Book Here
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: Raymond D. Vogler
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 22
Get Book Here
Book Description
As part of an NACA research program, an investigation by the transonic-bump method through a Mach range of 0.6 to 1.2 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. The wing of the semispan fuselage-wing combination had 45 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: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
Get Book Here
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: Alexander D. Hammond
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Get Book Here
Book Description
Author: Robert F. Thomson
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Get Book Here
Book Description
Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
Get Book Here
Book Description
As part of an NACA research 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 having various spans and spanwise locations. The wing of the semispan fuselage-wing combination had an unswept 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: Alexander D. Hammond
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 26
Get Book Here
Book Description
As a part of an NACA research program, an investigation by the transonic-bump method through a Mach number range of 0.6 to 1.15 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of a semispan wing-fuselage combination equipped with flap-type and spoiler-type controls.
Author: Rodger L. Naeseth
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 44
Get Book Here
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: Robert R. Graham
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Get Book Here
Book Description
