Wind Tunnel Investigation To Determine The Horizontal And Vertical Tail Contributions To The Static Lateral Stability Characteristics Of A Complete Model Swept Wing Configuration At High Subsonic Speeds

Author : James W. Wiggins
Publisher : Unknown
Page : 692 pages
File Size : 46,8 Mb
Release : 1956
Category : Airplanes
ISBN : STANFORD:36105024832094

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Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds by James W. Wiggins Pdf

An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.

Author : James W. Wiggins
Publisher : Unknown
Page : 34 pages
File Size : 46,6 Mb
Release : 1953
Category : Electronic
ISBN : OCLC:1109713085

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Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds by James W. Wiggins Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 940 pages
File Size : 45,6 Mb
Release : 1957
Category : Aeronautics
ISBN : RUTGERS:39030037544774

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Technical Note - National Advisory Committee for Aeronautics by United States. National Advisory Committee for Aeronautics Pdf

Author : M. Leroy Spearman
Publisher : Unknown
Page : 34 pages
File Size : 42,7 Mb
Release : 1957
Category : Airplanes
ISBN : UOM:39015086466235

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Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail by M. Leroy Spearman Pdf

An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.

Author : Anonim
Publisher : Unknown
Page : 620 pages
File Size : 47,9 Mb
Release : 1945
Category : Aeronautics
ISBN : UIUC:30112108399095

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Report by Anonim Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 128 pages
File Size : 44,8 Mb
Release : 1957
Category : Aeronautics
ISBN : STANFORD:36105024166147

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Annual Report - National Advisory Committee for Aeronautics by United States. National Advisory Committee for Aeronautics Pdf

Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Author : Anonim
Publisher : Unknown
Page : 630 pages
File Size : 40,8 Mb
Release : 1948
Category : Mechanics, Applied
ISBN : UCAL:C2682412

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Applied Mechanics Reviews by Anonim Pdf

Author : Howard F. Savage
Publisher : Unknown
Page : 662 pages
File Size : 55,6 Mb
Release : 1957
Category : Aerodynamics
ISBN : STANFORD:36105024832243

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The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 by Howard F. Savage Pdf

An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.

Author : Anonim
Publisher : Unknown
Page : 510 pages
File Size : 52,5 Mb
Release : 1956
Category : Aeronautics
ISBN : UIUC:30112008555440

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Technical Note by Anonim Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 508 pages
File Size : 45,8 Mb
Release : 1954
Category : Aeronautics
ISBN : IND:30000098603164

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Research Abstracts and Reclassification Notice by United States. National Advisory Committee for Aeronautics Pdf

Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 702 pages
File Size : 50,7 Mb
Release : 1949
Category : Aeronautics
ISBN : CORNELL:31924089884492

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Report - National Advisory Committee for Aeronautics by United States. National Advisory Committee for Aeronautics Pdf

Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1812 pages
File Size : 51,8 Mb
Release : 1960
Category : Government publications
ISBN : UCR:31210023919028

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Monthly Catalog of United States Government Publications by United States. Superintendent of Documents Pdf

Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1300 pages
File Size : 49,5 Mb
Release : 1978
Category : United States
ISBN : STANFORD:36105022657543

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Monthly Catalog of United States Government Publications, Cumulative Index by United States. Superintendent of Documents Pdf

Author : Robert H. Neely
Publisher : Unknown
Page : 96 pages
File Size : 52,9 Mb
Release : 1959
Category : Aeronautics
ISBN : UIUC:30112101598339

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Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds by Robert H. Neely Pdf

Author : Anonim
Publisher : Unknown
Page : 750 pages
File Size : 54,8 Mb
Release : 1949
Category : Aeronautics
ISBN : UVA:X004173285

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A Selected Listing of NASA Scientific and Technical Reports for ... by Anonim Pdf