Span Load Distributions Resulting Fron Angle Of Attack Rolling And Pitching For Tapered Swept Back Wings With Streamwise Tips
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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.
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.
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.
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.
A Selected Listing Of Nasa Scientific And Technical Reports For
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Author :
language : en
Publisher:
Release Date : 1949
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 1949 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 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.
Analogy Between Mass And Heat Transfer With Turbulent Flow
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Author : Edmund E. Callaghan
language : en
Publisher:
Release Date : 1953
Analogy Between Mass And Heat Transfer With Turbulent Flow written by Edmund E. Callaghan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Heat categories.
An analysis of combined heat and mass transfer from a flat plate has been made in terms of Prandtl's simpified physical concept of the turbulent boundary layer. The results of the analysis show that tor conditioins of reasonably small heat and mass transfer, the ratio of the mass- and heat-transfer coefficients is dependent on the Reynolds number of the boundary layer, the Prandtl number of the medium of diffusion, and the Schmidt number of the diffusing fluid in the medium of diffusion. For the particular case of water evaporating into air, the ratio of mass-transfer coefficient to heat-transfer coefficient is found to be slightly greater than unity.
Gust Load And Airspeed Data From One Type Of Four Engine Airplane On Five Routes From 1947 To 1954
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Author : Walter G. Walker
language : en
Publisher:
Release Date : 1955
Gust Load And Airspeed Data From One Type Of Four Engine Airplane On Five Routes From 1947 To 1954 written by Walter G. Walker and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Acceleration (Mechanics) categories.
This paper presents the results of an analysis of approximately 100,000 hours of V-G data from one type of four-engine civil transport airplane to determine the magnitude and frequency of occurrence of the gust loads and gusts. The data were obtained during routine operations from 1947 to 1954 on five different routes. The normal accelerations for each of the five operations may be expected to exceed the value corresponding to the limit-gust-load-factor increment, on the average, twice (once positive and once negative) within the range of 5,000,000 to 22,300,000 flight miles. A derived gust velocity of 50 feet per second was exceeded twice within the range of 600,000 to 1,900,000 flight miles. The gust loads of the present operations were less than the loads experienced by other four-engine civil transports previously investigated, but the differences are not significant. The present data indicated only small differences due to seasonal effects and different operational utilization.