Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications

Author: United States. Superintendent of Documents

Publisher:

Published: 1959

Total Pages: 2106

ISBN-13:

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February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.


Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2

Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2

Author: Marlowe D. Cassetti

Publisher:

Published: 1961

Total Pages: 104

ISBN-13:

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An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.


Aircraft Performance Theory for Pilots

Aircraft Performance Theory for Pilots

Author: Peter J. Swatton

Publisher: John Wiley & Sons

Published: 2008-04-30

Total Pages: 384

ISBN-13: 0470693053

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The new European Joint Aviation Requirements (JARs) lay down rules governing the minimum levels of performance which must be attained by every type of public transport aeroplane. These rules cover matters such as weight, altitude and temperature, take-off and landing distance, cruise flight level and speed, and descent angle and rate. The subject of aircraft performance forms an important part of all JAR Flight Crew Licensing examinations for commercial and airline transport pilot licences, and this book provides a clear but authoritative text on a difficult topic. It will also be of interest to commercial pilots needing to upgrade their annual ground test to JAR standards, and to flight planners, operations controllers and airport operators.


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.


Supercritical Wing Sections II

Supercritical Wing Sections II

Author: F. Bauer

Publisher: Springer Science & Business Media

Published: 2012-12-06

Total Pages: 304

ISBN-13: 3642489125

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This handbook is a sequel to an earlier volume entitled "A Theory of Supercritical Wing Sections, with Computer Programs and Examples." Since the completion of the first volume, which we shall refer to as Volume I (cf. [ll), some effort has been made to improve our airfoil design program. A number of more desirable air foils have been designed. In addition several of our wing sections have been tested in wind tunnels. We should like to make this material available here, since it is more convenient to use the design program in conjunction with data for a fairly broad range of examples. Moreover, we have developed new analysis programs that supersede our previous work. Chapter I is devoted to a brief discussion of the mathematics involved in our additions and modifications. There is only a mini mum emphasis on theory, since the representation of important physical phenomena such as boundary layer shock wave interaction and separation is partly empirical. It is our contention, however, that the computer programs provide a better simulation than might have been expected. Chapter II presents numerical results found by our new methods, as well as comparisons with experimental data. Chapter III contains a discussion of the use of the program together with Fortran listings.