Aerodynamic Loads On An Isolated Shrouded Propeller Configuration Of Angles Of Attack From 10 Degrees To 110 Degrees
DOWNLOAD
FREE 30 Days
Download Aerodynamic Loads On An Isolated Shrouded Propeller Configuration Of Angles Of Attack From 10 Degrees To 110 Degrees PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Aerodynamic Loads On An Isolated Shrouded Propeller Configuration Of Angles Of Attack From 10 Degrees To 110 Degrees book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
Aerodynamic Loads On An Isolated Shrouded Propeller Configuration Of Angles Of Attack From 10 Degrees To 110 Degrees
DOWNLOAD
FREE 30 Days
Author : Kalman J. Grunwald
language : en
Publisher:
Release Date : 1962
Aerodynamic Loads On An Isolated Shrouded Propeller Configuration Of Angles Of Attack From 10 Degrees To 110 Degrees written by Kalman J. Grunwald and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Propulsion systems categories.
U S Government Research Reports
DOWNLOAD
FREE 30 Days
Author :
language : en
Publisher:
Release Date : 1962
U S Government Research Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Science categories.
Advances In Computational Methods And Technologies In Aeronautics And Industry
DOWNLOAD
FREE 30 Days
Author : Dietrich Knoerzer
language : en
Publisher: Springer Nature
Release Date : 2022-12-12
Advances In Computational Methods And Technologies In Aeronautics And Industry written by Dietrich Knoerzer and has been published by Springer Nature this book supported file pdf, txt, epub, kindle and other format this book has been release on 2022-12-12 with Technology & Engineering categories.
This book provides research results using computational methods for fluid dynamics and engineering problems in aeronautics and other scientific and industrial applications. It gives an overview on the state of the art and the technology trends requiring advanced computational methods towards digitization in industrial and scientific processes. The chapters are based on Special Technology Sessions of the WCCM-ECCOMAS Virtual Congress 2021.
Bibliography Of Scientific And Industrial Reports
DOWNLOAD
FREE 30 Days
Author :
language : en
Publisher:
Release Date : 1962
Bibliography Of Scientific And Industrial Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Research categories.
Index Aeronauticus
DOWNLOAD
FREE 30 Days
Author :
language : en
Publisher:
Release Date : 1962
Index Aeronauticus written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Aeronautics categories.
Usaf Stability And Control Datcom
DOWNLOAD
FREE 30 Days
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.
Aerodynamic Characteristics Of A Powered Semispan Tilting Shrouded Propeller Vtol Model In Hovering And Transition Flight
DOWNLOAD
FREE 30 Days
Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1962
Aerodynamic Characteristics Of A Powered Semispan Tilting Shrouded Propeller Vtol Model In Hovering And Transition Flight 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 1962 with Aerodynamics categories.
"An investigation of the aerodynamic characteristics of a powered semispan tilting-shrouded-propeller configuration has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 2.67 (based on wing span of 60 inches), a taper ratio of 0.67, and an NACA 2418 airfoil section with a 15-inch-diameter shrouded propeller mounted on the tip. The test results show that large nose-up pitching moments are obtained at transitional speeds of about 40 knots and duct angle of about 70°. Decelerating flight procedures further increases in the nose-up moment. Ground proximity reduces the nose-up pitching moments. The large nose-up moments can be trimmed by use of duct-exit control vanes. The results show that unloading the duct (shroud) by flying at a wing angle of attack of 15° reduces the power required by about 30 percent at 50 knots. Duct-lip stall produces large increases in power required. The results in general show that full-scale aerodynamic simulation can be made with small-scale wind-tunnel models if duct-lip separation at low Reynolds numbers is avoided."--Summary.
Investigation Of The Aerodynamic Characteristics Of A Model Wing Propeller Combination And Of The Wing And Propeller Separately At Angles Of Attack Up To 90
DOWNLOAD
FREE 30 Days
Author : John W. Draper
language : en
Publisher:
Release Date : 1954
Investigation Of The Aerodynamic Characteristics Of A Model Wing Propeller Combination And Of The Wing And Propeller Separately At Angles Of Attack Up To 90 written by John W. Draper and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aerodynamics categories.
This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Effect Of Propeller Location And Flap Deflection On The Aerodynamic Characteristics Of A Wing Propeller Combination For Angles Of Attack From 0 To 80 Degrees
DOWNLOAD
FREE 30 Days
Author : William A. Newsom
language : en
Publisher:
Release Date : 1957
Effect Of Propeller Location And Flap Deflection On The Aerodynamic Characteristics Of A Wing Propeller Combination For Angles Of Attack From 0 To 80 Degrees written by William A. Newsom 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.
An investigation has been made to determine the effect of propeller location and flap deflection on the lift, drag, and pitching-moment characteristics of a wing-propeller combination over an angle-of-attack range from 0 to 80 degrees. The model had four propellers, the slipstream from which covered practically the entire span of the wing. The wing had a 30-percent-chord slotted flap and an 8.5-percent-chord slat. Data were obtained for flap deflections of 0, 20, 40, and 60 degrees with the slat off and on. For one propeller position the power input to the model was measured and tuft studies of the flow on the wing were made. The data are analyzed to assess the feasibility, from consideration of stability and control, of a tilting-wing vertical-take-off-and-landing airplane with the wing pivoted behind the primary wing structure to provide a desirable structural configuration. The main object of the investigation was to determine whether advantage might be taken of the forward shift of the center of gravity of the airplane, as the wing is tilted from an angle of attack of 90 to 0 degrees, to minimize the change in trim pitching moment throughout the transition speed range for such a configuration. The results indicate that with proper propeller position and programming of flap deflection, it is possible to design a configuration of this type in which essentially no change in trim is required throughout the transition from hovering to normal unstalled forward flight.
The Effects Of Compressibility On The Upwash At The Propeller Planes Of A Four Engine Tractor Airplane Configuration Having A Wing With 40 Degrees Of Sweepback And An Aspect Ratio Of 10
DOWNLOAD
FREE 30 Days
Author : Armando E. Lopez
language : en
Publisher:
Release Date : 1953
The Effects Of Compressibility On The Upwash At The Propeller Planes Of A Four Engine Tractor Airplane Configuration Having A Wing With 40 Degrees Of Sweepback And An Aspect Ratio Of 10 written by Armando E. Lopez and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aerodynamics categories.
The results indicate that for Mach numbers up to 0.60 the upwash angles can be predicted accurately by the available theoretical methods. At Mach numbers above 0.60 the experimental values were less than those predicted by theory and this difference increased with increasing Mach number.