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
Title 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 PDF eBook
Author Ralph P. Bielat
Publisher
Pages 44
Release 1951
Genre Aerodynamics, Transonic
ISBN

Download 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 Book in PDF, Epub and Kindle

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.

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
Title 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 PDF eBook
Author Ralph P. Bielat
Publisher
Pages 38
Release 1958
Genre Aerodynamics, Transonic
ISBN

Download 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 Book in PDF, Epub and Kindle

Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports
Title Scientific and Technical Aerospace Reports PDF eBook
Author
Publisher
Pages 456
Release 1995
Genre Aeronautics
ISBN

Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Index of Reports on Aeronautical Research

Index of Reports on Aeronautical Research
Title Index of Reports on Aeronautical Research PDF eBook
Author United States. National Advisory Committee for Aeronautics
Publisher
Pages 42
Release 1940
Genre Aeronautics
ISBN

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Wind Tunnel Wall Correction

Wind Tunnel Wall Correction
Title Wind Tunnel Wall Correction PDF eBook
Author B. F. R. Ewald
Publisher
Pages 578
Release 1998
Genre Aerodynamics
ISBN

Download Wind Tunnel Wall Correction Book in PDF, Epub and Kindle

This report was compiled by an international team of wind tunnel wall correction experts. It presents the present state of the art in wind tunnel wall corrections with a special emphasis given to the description of modern wall correction methods based on Computational Fluid Dynamics. This AGARDograph was planned by the AGARD Fluid Dynamics Panel to be a modern sequel of the successful AGARDograph 109 "Subsonic Wind Tunnel Wall Corrections", which was published in 1966. AGARDogaph 109 is still valid and continues to be used to provide wall corrections in many wind tunnels. Nevertheless, in the thirty two years since the publication of AGARDograph 109, much work has been done on the subject, and the influence of the new tool of numerical fluid dynamics was so strong, that a sequel to AGARDograph 109 was considered to be necessary.

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
Title 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 PDF eBook
Author Jack F. Runckel
Publisher
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.

Preliminary Report on Flight Tests of an Airplane Having Exhaust-heated Wings

Preliminary Report on Flight Tests of an Airplane Having Exhaust-heated Wings
Title Preliminary Report on Flight Tests of an Airplane Having Exhaust-heated Wings PDF eBook
Author Lewis A. Rodert
Publisher
Pages 42
Release 1941
Genre Airplanes
ISBN

Download Preliminary Report on Flight Tests of an Airplane Having Exhaust-heated Wings Book in PDF, Epub and Kindle

Flights have been made with an airplane in icing conditions in order to test the effect of exhaust heat applied to the wings as a means of preventing ice formations. Other ice-prevention equipment, including an exhaust gas-heated pitot-static head, hot-air-heated windshield, and an inflatable de-icer of recent design, were also tested.