Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section
Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section

Author: William C. Sleeman

Publisher:

Published: 1949

Total Pages: 34

ISBN-13:

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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 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section
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. Myers

Publisher:

Published: 1949

Total Pages: 36

ISBN-13:

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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
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. Runckel

Publisher:

Published: 1956

Total Pages: 104

ISBN-13:

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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.

An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47© Sweepback, Aspect Ratio 3.5, and Taper Ratio 0.2 in the Slotted Test Section of the Langley 8-foot High-speed Tunnel
An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47© Sweepback, Aspect Ratio 3.5, and Taper Ratio 0.2 in the Slotted Test Section of the Langley 8-foot High-speed Tunnel

Author: Ralph P. Bielat

Publisher:

Published: 1951

Total Pages: 44

ISBN-13:

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Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.

Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body
Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body

Author: Donald D. Arabian

Publisher:

Published: 1960

Total Pages: 84

ISBN-13:

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The aerodynamic load characteristics of a wing-body combination were determined experimentally at Mach numbers from 0.80 to 1.03 for angles of attack up to 26 degrees. Two wings, both with 30 degrees sweep of the quarter-chord line, taper ratio of 0.2, aspect ratio of 3, and thickness of 4 percent chord, but of different types of construction, were tested. One wing was of solid steel and the other was of plastic with an inner steel core ...

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
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. RUNCKEL

Publisher:

Published: 1961

Total Pages: 1

ISBN-13:

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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 was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).

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
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 Spearman

Publisher:

Published: 1957

Total Pages: 34

ISBN-13:

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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.

Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01
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. Lord

Publisher:

Published: 1957

Total Pages: 52

ISBN-13:

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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.

Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6
Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6

Author: George W. Jones

Publisher:

Published: 1957

Total Pages: 22

ISBN-13:

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A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.