Experimental Investigation Of Temperature Recovery Factors On Bodies Of Revolution At Supersonic Speeds
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Experimental Investigation Of Temperature Recovery Factors On Bodies Of Revolution At Supersonic Speeds
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Author : William R. Wimbrow
language : en
Publisher:
Release Date : 1949
Experimental Investigation Of Temperature Recovery Factors On Bodies Of Revolution At Supersonic Speeds written by William R. Wimbrow and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerodynamics, Supersonic categories.
Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.
Experimental Investigation Of Flutter Of A Propeller With Clark Y Section Operating At Zero Forward Velocity At Positive And Negative Blade Angle Settings
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Author : John E. Baker
language : en
Publisher:
Release Date : 1949
Experimental Investigation Of Flutter Of A Propeller With Clark Y Section Operating At Zero Forward Velocity At Positive And Negative Blade Angle Settings written by John E. Baker and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerofoils categories.
The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment and the flutter speed increased considerably in this region with decreasing pressure. Over the rest of the pitch range, the flutter speeds were much lower and varied little with pressure.
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.
Annual Report Of The National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1954
Annual Report Of The 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 1954 with Aeronautics categories.
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Report National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1950
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 1950 with Aeronautics categories.
Report
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1951
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 1951 with Aeronautics categories.
Two Dimensional Flow On General Surfaces Of Revolution In Turbomachines
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Author : John D. Stanitz
language : en
Publisher:
Release Date : 1952
Two Dimensional Flow On General Surfaces Of Revolution In Turbomachines written by John D. Stanitz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Air flow categories.
A method of analysis is developed for two dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-blade impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.
Index Of Naca Technical Publications
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1959
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 1959 with Aeronautics categories.
Technical Note
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Author :
language : en
Publisher:
Release Date : 1953
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 1953 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.