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.

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.