Author: Arvo A. Luoma
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
Book Description
Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination with a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2
Author: Arvo A. Luoma
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
Book Description
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35©, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Book Description
Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees and 60 Degrees
Author: William B. Jr Kemp
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
Book Description
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 6 , Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: William C. Sleeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Aerodynamic Studies
Author: Zbiginew Krzywoblocki
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132
Book Description
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 29
Book Description
This paper presents the results of the investigation of a wing-alone and a wing-fuselage combination employing a wing with the quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for the wing-alone and wing-body configurations. Effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 29
Book Description
This paper presents the results of the investigation of a wing-alone and a wing-fuselage combination employing a wing with the quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for the wing-alone and wing-body configurations. Effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Aerodynamic Characteristics at Transonic Speeds of a Wing Having a 45 Degree Sweep, Aspect Ratio 8, Taper Ratio 0.45, and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip
Author: William D. Morrison
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
Book Description
An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
Book Description
An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section - Transonic-bump Method
Author: Thomas J. Jr King
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Aifoil Section - Transonic-bump Method
Author: William C. Jr Sleeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Author: Joseph Weil
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Book Description
As part of an NACA research program, a series of wing-body combinations are being investigated in the Langley high-speed 7- by 10-foot tunnel up to a Mach number of 1.18 utilizing the transonic bump.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Book Description
As part of an NACA research program, a series of wing-body combinations are being investigated in the Langley high-speed 7- by 10-foot tunnel up to a Mach number of 1.18 utilizing the transonic bump.