Author: Alexander D. Hammond
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Lateral-control Investigation of Flap-type Controls on a Wing with Unswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Alexander D. Hammond
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
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
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
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.
Lateral-control Investigation of Flap-type Controls on a Wing with Upswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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.
Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Raymond D. Vogler
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 22
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.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 22
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.
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Book Description
Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Raymond D. Vogler
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 21
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.
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 21
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.
Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 22
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.
Lateral-control Investigation of Flat-type Controls on a Wing Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Robert F. Thomson
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Lateral-control Investigation of Flap-type and Spoiler-type Controls on a Wing with Quarter-chord-line Sweepback of 60 Degrees, Aspect Ratio 2, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Alexander D. Hammond
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 26
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.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 26
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.