A Study Of The Flow Over A 45 Sweptback Wing Fuselage Combination At Transonic Mach Numbers PDF Download
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Author | : Richard T. Whitcomb |
Publisher | : |
Total Pages | : 68 |
Release | : 1952 |
Genre | : Aerodynamics |
ISBN | : |
Download A Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers Book in PDF, ePub and Kindle
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.
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
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Author | : Richard T. Whitcomb |
Publisher | : |
Total Pages | : 60 |
Release | : 1952 |
Genre | : |
ISBN | : |
Download A Study of the Flow Over a 45 Degree Sweptback Wing-fuselage Combination at Transonic Mach Numbers Book in PDF, ePub and Kindle
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.
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
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.
Author | : Donald L. Loving |
Publisher | : |
Total Pages | : 52 |
Release | : 1952 |
Genre | : Airplanes |
ISBN | : |
Download Transonic Wind-tunnel Investigation of the Interference Between a 45© Sweptback Wing and a Systematic Series of Four Bodies Book in PDF, ePub and Kindle
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 388 |
Release | : 1959 |
Genre | : Aeronautics |
ISBN | : |
Download Index of NACA Technical Publications Book in PDF, ePub and Kindle
Author | : Jack F. Runckel |
Publisher | : |
Total Pages | : 98 |
Release | : 1961 |
Genre | : Aerodynamics |
ISBN | : |
Download Investigation at Transonic Speeds of the Loading Over a 40 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
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 508 |
Release | : 1954 |
Genre | : Aeronautics |
ISBN | : |
Download Research Abstracts and Reclassification Notice Book in PDF, ePub and Kindle