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
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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
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Author : James W. Wiggins
language : en
Publisher:
Release Date : 1956
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 written by James W. Wiggins and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Airplanes categories.
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.
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
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Author : James W. Wiggins
language : en
Publisher:
Release Date : 1953
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 written by James W. Wiggins and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with categories.
Technical Note National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Technical Note National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aeronautics categories.
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
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1957
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 written by M. Leroy Spearman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
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.
Report
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Author :
language : en
Publisher:
Release Date : 1945
Report written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with Aeronautics categories.
Annual Report
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1953
Annual Report written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aeronautics categories.
Annual Report National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Annual Report National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aeronautics categories.
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Applied Mechanics Reviews
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Author :
language : en
Publisher:
Release Date : 1948
Applied Mechanics Reviews written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Mechanics, Applied categories.
The Subsonic Static Aerodynamic Characteristics Of An Airplane Model Having A Triangular Wing Of Aspect Ratio 3
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Author : Howard F. Savage
language : en
Publisher:
Release Date : 1957
The Subsonic Static Aerodynamic Characteristics Of An Airplane Model Having A Triangular Wing Of Aspect Ratio 3 written by Howard F. Savage and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamics categories.
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.
Technical Note
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Author :
language : en
Publisher:
Release Date : 1956
Technical Note written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aeronautics categories.