Wing On And Wing Off Longitudinal Characteristics Of An Airplane Configuration Having A Thin Unswept Tapered Wing Of Aspect Ratio 3 As Obtained From Rocket Propelled Models At Mach Numbers From 0 8 To 1 4
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Index Of Naca Technical Publications
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Index Of Naca Technical Publications 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.
A Selected Listing Of Nasa Scientific And Technical Reports For
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Author :
language : en
Publisher:
Release Date : 1957
A Selected Listing Of Nasa Scientific And Technical Reports For written by 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.
The Journal Of The Royal Aeronautical Society
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Author :
language : en
Publisher:
Release Date : 1960
The Journal Of The Royal Aeronautical Society written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aeronautics categories.
Wing On And Wing Off Longitudinal Characteristics Of An Airplane Configuration Having A Thin Unswept Tapered Wing Of Aspect Ratio 3 As Obtained From Rocket Propelled Models At Mach Numbers From 0 8 To 1 4
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Author : Clarence L. Gillis
language : en
Publisher:
Release Date : 1951
Wing On And Wing Off Longitudinal Characteristics Of An Airplane Configuration Having A Thin Unswept Tapered Wing Of Aspect Ratio 3 As Obtained From Rocket Propelled Models At Mach Numbers From 0 8 To 1 4 written by Clarence L. Gillis and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with categories.
Wing On And Wing Off Longitudinal Characteristics Of An Airplane Configuration Having A Thin Unswept Wing Of Aspect Ratio 3 As Obtained From Rocket Propelled Models At Mach Numbers From 0 8 To 1 4
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Author : Clarence L. Gillis
language : en
Publisher:
Release Date : 1959
Wing On And Wing Off Longitudinal Characteristics Of An Airplane Configuration Having A Thin Unswept Wing Of Aspect Ratio 3 As Obtained From Rocket Propelled Models At Mach Numbers From 0 8 To 1 4 written by Clarence L. Gillis and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Mach number categories.
Static Longitudinal Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configurations
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1961
Static Longitudinal Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configurations written by Kenneth W. Goodson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Stability of airplanes, Longitudinal categories.
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1961
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration written by Kenneth W. Goodson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Stability of airplanes, Lateral categories.
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 75 To 1 5 Of An Airplane Configuration Having A 60 Degrees Swept Wing Of Aspect Ratio 2 24 As Obtained From Rocket Propelled Model
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Author : A. James Vitale
language : en
Publisher:
Release Date : 1952
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 75 To 1 5 Of An Airplane Configuration Having A 60 Degrees Swept Wing Of Aspect Ratio 2 24 As Obtained From Rocket Propelled Model written by A. James Vitale and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with categories.
Static Longitudinal Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configurations
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1957
Static Longitudinal Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configurations written by Kenneth W. Goodson 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.
The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best over-all characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Investigation Of Transonic Flutter Characteristics Of A Thin 10 Degree Sweptback Wing Having An Aspect Ratio Of 4 And A Taper Ratio Of 0 6
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Author : George W. Jones
language : en
Publisher:
Release Date : 1957
Investigation Of Transonic Flutter Characteristics Of A Thin 10 Degree Sweptback Wing Having An Aspect Ratio Of 4 And A Taper Ratio Of 0 6 written by George W. Jones 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, Transonic categories.
A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.