Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps
DOWNLOAD
Download Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps 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
Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps
DOWNLOAD
Author : James C. Sivells
language : en
Publisher:
Release Date : 1948
Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps written by James C. Sivells and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aerofoils categories.
An investigation has been conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings had zero sweep, an aspect ratio of 9, and a ratio of root to tip chord of 2.5. Wings were tested with and without a representative fuselage and with and without leading-edge roughness.
Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps
DOWNLOAD
Author : James C. Sivells
language : en
Publisher:
Release Date : 1951
Investigation In The Langley 19 Foot Pressure Tunnel Of Two Wings Of Naca 65 210 And 64 210 Airfoil Sections With Various Type Flaps written by James C. Sivells and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with categories.
Technical Note
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1948
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 1948 with Aeronautics categories.
Index Of Naca Technical Publications
DOWNLOAD
Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1952
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 1952 with Aeronautics categories.
A Selected Listing Of Nasa Scientific And Technical Reports For
DOWNLOAD
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.
Annual Report National Advisory Committee For Aeronautics
DOWNLOAD
Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Annual 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 1957 with Aeronautics categories.
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Report
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1957
Report written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aeronautics categories.
Report National Advisory Committee For Aeronautics
DOWNLOAD
Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1947
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 1947 with Aeronautics categories.
Method For Calculating Lift Distribtutions For Unswept Wings With Flaps Or Ailerons By Use Of Nonlinear Section Lift Data
DOWNLOAD
Author : James C. Sivells
language : en
Publisher:
Release Date : 1951
Method For Calculating Lift Distribtutions For Unswept Wings With Flaps Or Ailerons By Use Of Nonlinear Section Lift Data written by James C. Sivells and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Ailerons categories.
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.
Simulated Altitude Investigations Of Performance Of Tubular Aircraft Oil Coolers
DOWNLOAD
Author : S. V. Manson
language : en
Publisher:
Release Date : 1948
Simulated Altitude Investigations Of Performance Of Tubular Aircraft Oil Coolers written by S. V. Manson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Airplanes categories.
For constant oil-inlet temperature, congealing of the oil at each altitude produces an initial decrease of about 5 to 10 percent of the maximum heat dissipation attained at the altitude and is followed by constancy of oil hat dissipation as air flow increases.