A Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers
A Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers

Author: Richard T. Whitcomb

Publisher:

Published: 1952

Total Pages: 68

ISBN-13:

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Abstract: Pressure distributions, tuft patterns, and schlieren surveys have been obtained for a 45° sweptback wing-fuselage combination in the Langley 8-foot transonic tunnel at transonic Mach numbers to 1.11 and angles of attack to 20°. The results provide an indication at transonic Mach numbers of the nature of the formation of shock waves on the wing and fuselage, wing-fuselage interference, and the development of separation and the separation vortex.

Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers
Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers

Author: Langley Aeronautical Laboratory

Publisher: Hassell Street Press

Published: 2021-09-09

Total Pages: 68

ISBN-13: 9781014240347

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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 Experimental Study of a Method of Designing the Sweptback-wing - Fuselage Juncture for Reducing the Drag at Transonic Speeds
An Experimental Study of a Method of Designing the Sweptback-wing - Fuselage Juncture for Reducing the Drag at Transonic Speeds

Author: Robert R. Howell

Publisher:

Published: 1955

Total Pages: 30

ISBN-13:

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An investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.84 and 1.32 at an angle of attack of zero degrees to determine the pressure-drag reductions attainable on a sweptback-wing - fuselage configuration tested consisted of a 45 degree sweptback wing of aspect ratio 4 in combination with a fineness-ratio-6.7 body. The results indicate that the pressure drag of a practical sweptback-wing - body configuration depends on the body cross-sectional shape as well as upon the longitudinal distribution of cross-sectional area.

Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies
Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies

Author: Thomas C. Kelly

Publisher:

Published: 1957

Total Pages: 86

ISBN-13:

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Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.

Transonic Investigation of Internal-flow Characteristics of a Square-shaped Scoop Inlet Mounted at Three Chordwise Positions Above a High 45 Degree Sweptback Wing and Body Combination
Transonic Investigation of Internal-flow Characteristics of a Square-shaped Scoop Inlet Mounted at Three Chordwise Positions Above a High 45 Degree Sweptback Wing and Body Combination

Author: Arvid L. Keith

Publisher:

Published: 1957

Total Pages: 35

ISBN-13:

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An investigation has been made in the Langley transonic blowdown tunnel at Mach numbers of 1.04, 1.28, and 1.42 to determine the internal-flow characteristics of three top-mounted scoop inlets with rounded lips. The inlets, which were of square cross section, were mounted at the leading edge, midchord, or trailing edge of the high 45 degree sweptback 6-percent-thick wing. The rearmost position without the wing installed was also studied. The test results showed that the inlet located at the wing leading edge achieved normal-shock total-pressure ratios without boundary-layer control for all Mach numbers and angles of attack. Rearward movement of the inlet over the wing effected losses of as much as 9 percent of the free-stream total pressure, compared with the leading-edge position, and increases in flow distortion up to 42 percent of the average inlet total pressure. The presence of the wing apparently had little effect on the internal-flow characteristics of the rearmost inlet for the Mach number and angle-of-attack ranges investigated.