Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 258
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 258
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Book Description
Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01
Author: Douglas R. LordPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
Book Description
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section
Author: Boyd C. MyersPublisher:
ISBN:
Category : Airplane
Languages : en
Pages : 36
Book Description
This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, 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 the publishing of these data, only a brief analysis is included.
Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections
Author: Jack F. RunckelPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 104
Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section
Author: William C. SleemanPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 34
Book Description
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were 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 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. SleemanPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Book Description
Pressure Distributions and Aerodynamic Characteristics of Several Spoiler Controls on a 40 Degree Sweptback Wing at a Mach Number of 1.61
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 70
Book Description
Low-speed Characteristics in Pitch of a 340 Sweptforward Wing with Circular-arc Airfoil Sections
Author: D. William ConnerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 70
Book Description
Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
