[PDF] Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method - eBooks Review

Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method


Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method
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Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method


Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1948

Longitudinal Stability And Control Characteristics At Transonic Speeds Of A Semispan Airplane Model Having A 45 Degrees Sweptback Wing And Tail As Obtained By The Transonic Bump Method 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 1948 with categories.




Usaf Stability And Control Datcom


Usaf Stability And Control Datcom
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Author : Douglas Aircraft Company
language : en
Publisher:
Release Date : 1975

Usaf Stability And Control Datcom written by Douglas Aircraft Company and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Airplanes categories.




Journal Of The Royal Aeronautical Society


Journal Of The Royal Aeronautical Society
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Author :
language : en
Publisher:
Release Date : 1954

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 1954 with Aeronautics categories.




Journal Of The Royal Aeronautical Society


Journal Of The Royal Aeronautical Society
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Author : Royal Aeronautical Society
language : en
Publisher:
Release Date : 1954

Journal Of The Royal Aeronautical Society written by Royal Aeronautical Society and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aeronautics categories.




Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Swept Back Tail From Tests At Transonic Speeds By The Naca Wing Flow Method


Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Swept Back Tail From Tests At Transonic Speeds By The Naca Wing Flow Method
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Author : John A. Zalovcik
language : en
Publisher:
Release Date : 1947

Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Swept Back Tail From Tests At Transonic Speeds By The Naca Wing Flow Method written by John A. Zalovcik and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with Aerodynamics, Transonic categories.


An investigation was made by the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane model having a wing of conventional plan form and a horizontal tail swept back 45 degrees. The wing and tail had NACA 65-series airfoil sections with thicknesses of 10 and 8 percent chord, respectively. The model was mounted in such a way as to permit it to assume a position of zero pitching moment about a center of gravity at 27 percent of the mean aerodynamic chord. Measurements were made of lift and angle of attack for trim for several stabilizer and elevator settings.



Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds As Obtained By The Transonic Bump Method


Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds As Obtained By The Transonic Bump Method
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Author : Joseph Weil
language : en
Publisher:
Release Date : 1948

Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds As Obtained By The Transonic Bump Method written by Joseph Weil and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with categories.




Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Sweptback Wing And Tail From Tests At Transonic Speeds By The Naca Wing Flow Method


Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Sweptback Wing And Tail From Tests At Transonic Speeds By The Naca Wing Flow Method
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Author : Richard H. Sawyer
language : en
Publisher:
Release Date : 1948

Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model With A Sweptback Wing And Tail From Tests At Transonic Speeds By The Naca Wing Flow Method written by Richard H. Sawyer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with categories.




Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds From Tests By The Naca Wing Flow Method


Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds From Tests By The Naca Wing Flow Method
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Author : John A. Zalovcik
language : en
Publisher:
Release Date : 1946

Longitudinal Stability And Control Characteristics Of A Semispan Airplane Model At Transonic Speeds From Tests By The Naca Wing Flow Method written by John A. Zalovcik and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1946 with categories.




Longitudinal Stability Characteristics At Transonic Speeds Of A Rocket Propelled Model Of An Airplane Configuration Having A 45 Degree Swept Wing Of Aspect Ratio 6 0


Longitudinal Stability Characteristics At Transonic Speeds Of A Rocket Propelled Model Of An Airplane Configuration Having A 45 Degree Swept Wing Of Aspect Ratio 6 0
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Author : John C. Jr McFall
language : en
Publisher:
Release Date : 1954

Longitudinal Stability Characteristics At Transonic Speeds Of A Rocket Propelled Model Of An Airplane Configuration Having A 45 Degree Swept Wing Of Aspect Ratio 6 0 written by John C. Jr McFall and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with categories.




Longitudinal Stability And Control Characteristics At High Subsonic Speeds Of Two Models Of A Transonic Research Airplane With Wings And Horizontal Tails Of Aspect Ratios 4 2 And 2


Longitudinal Stability And Control Characteristics At High Subsonic Speeds Of Two Models Of A Transonic Research Airplane With Wings And Horizontal Tails Of Aspect Ratios 4 2 And 2
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Author : Arvo A. Luoma
language : en
Publisher:
Release Date : 1950

Longitudinal Stability And Control Characteristics At High Subsonic Speeds Of Two Models Of A Transonic Research Airplane With Wings And Horizontal Tails Of Aspect Ratios 4 2 And 2 written by Arvo A. Luoma and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Airplanes categories.


An investigation was made in the Langley 8-foot high-speed tunnel of two transonic research airplane models for Mach numbers up to approximately 0.95. The test Reynolds number at the highest speed was 1,600,000 for one model and 2,300,000 for the other model. The models were 1/16-schale and were supported in the tunnel on a sting. The wing and horizontal tail of one model were both of aspect ratio 4.2; the wing and horizontal tail of the other model were both of aspect ratio 2. The same fuselage and vertical tail were used on both models. The sweep of the 50-percent-chord line of the wings was zero degrees; the sweep of the 75-percent-chord line of the horizontal tails was zero degrees. Both wings had NACA 65-110 airfoil sections and both horizontal tails had NACA 65-008 airfoil sections. Lift drag, and pitching moment were determined by means of a strain-gage balance within the fuselage. Tare measurements were made to eliminate the interference effect of the sting.