Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips Supersonic Leading And Trailing Edges
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Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips
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Author : John C. Martin
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips written by John C. Martin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Airplanes categories.
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constant angle of attack, from steady rolling, and from steady pitching were calculated for a series of thin sweptback tapered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of this analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with the various design parameters are also presented.
Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips Supersonic Leading And Trailing Edges
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Author :
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips Supersonic Leading And Trailing Edges written by 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.
Span Load Distributions Resulting Fron Angle Of Attack Rolling And Pitching For Tapered Swept Back Wings With Streamwise Tips
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Author : John C. Martin
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting Fron Angle Of Attack Rolling And Pitching For Tapered Swept Back Wings With Streamwise Tips written by John C. Martin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aerodynamic load categories.
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constsnt angle of attack, from steady rolling and from steady pitching were calculated for a series of thin sweptback tempered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distribution of circulation with the various design parameters are also presented.
Analysis Of Multicell Delta Wings On Cal Tech Analog Computer
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Author : Richard H. MacNeal
language : en
Publisher:
Release Date : 1953
Analysis Of Multicell Delta Wings On Cal Tech Analog Computer written by Richard H. MacNeal and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Airplanes categories.
Deflections and all internal forces have been calculated for concentrated static loads. Vibration modes are also presented. The effects of neglecting shearing strains in the ribs and spars and also of assuming the ribs to be rigid have been investigated by modifying the electric circuits to correspond to these simplifications.
Aerodynamics Of Tactical Weapons To Mach Number 8 And Angle Of Attack 180
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Author : Leroy Devan
language : en
Publisher:
Release Date : 1980
Aerodynamics Of Tactical Weapons To Mach Number 8 And Angle Of Attack 180 written by Leroy Devan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Angle of attack (Aerodynamics). 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 : 1956
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 1956 with Aeronautics categories.
Index Of Naca Technical Publications
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1954
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 1954 with Aeronautics categories.
Technical Note
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Author :
language : en
Publisher:
Release Date : 1952
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 1952 with Aeronautics categories.
Charts For Estimating Rotor Blade Flapping Motion Of High Performance Helicopters
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Author : Robert J. Tapscott
language : en
Publisher:
Release Date : 1956
Charts For Estimating Rotor Blade Flapping Motion Of High Performance Helicopters written by Robert J. Tapscott and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Charts, diagrams, etc categories.
Theoretically derived charts showing steady-state and first- and second-harmonic flapping coefficients are presented for helicopter rotors having hinged rectangular blades with a linear twist of 0, -8, and -16 degrees. The charts, showing the rotor flapping coefficients for combinations of inflow ratio and blade pitch angle, are presented for tip-speed ratios ranging from 0.05 to 0.50.
Span Load Distributions Resulting From Constant Angle Of Attack Steady Rolling Velocity Steady Pitching Velocity And Constant Vertical Acceleration For Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges And Supersonic Trailing Edges
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Author :
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting From Constant Angle Of Attack Steady Rolling Velocity Steady Pitching Velocity And Constant Vertical Acceleration For Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges And Supersonic Trailing Edges written by 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.
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.