A Study Of The Flow Over A 45 Sweptback Wing Fuselage Combination At Transonic Mach Numbers PDF Download

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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:
Total Pages: 68
Release: 1952
Genre: Aerodynamics
ISBN:

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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
Total Pages: 68
Release: 2021-09-09
Genre:
ISBN: 9781014240347

Download Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers Book in PDF, ePub and Kindle

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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:
Total Pages: 104
Release: 1956
Genre: Aerodynamic load
ISBN:

Download 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 Book in PDF, ePub and Kindle

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.


A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance

A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance
Author: Donald L. Loving
Publisher:
Total Pages: 92
Release: 1961
Genre: Aerodynamics
ISBN:

Download A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance Book in PDF, ePub and Kindle


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:
Total Pages: 30
Release: 1955
Genre: Aerodynamics, Transonic
ISBN:

Download An Experimental Study of a Method of Designing the Sweptback-wing - Fuselage Juncture for Reducing the Drag at Transonic Speeds Book in PDF, ePub and Kindle

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.


Index of NACA Technical Publications

Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 388
Release: 1959
Genre: Aeronautics
ISBN:

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Research Abstracts and Reclassification Notice

Research Abstracts and Reclassification Notice
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 508
Release: 1954
Genre: Aeronautics
ISBN:

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