Upon A Trailing Edge
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Upon A Trailing Edge
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Author : Michael Joy
language : en
Publisher: Troubador Publishing Ltd
Release Date : 2015-11-28
Upon A Trailing Edge written by Michael Joy and has been published by Troubador Publishing Ltd this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-11-28 with Transportation categories.
This is a story of aviation, risk and the heart of the pilot. Four out of five fatal aircraft accidents are due to human error; three out of five to pilot error. This book examines the technical aspects of these issues from the viewpoint of one of the UK's most experienced aviation cardiologists. It spans the end of the Second World War through teaching cardiology in aviation on behalf of the International Civil Aviation Organisation (ICAO) worldwide, via a history of powered flight, time in the cadet force, a flying scholarship on a Tiger Moth, training to be a doctor, later a cardiologist, and owing a series of aircraft. Michael Joy was appointed as cardiologist to the Civil Aviation Authority (CAA) in 1974 to assist the regulator in the development of standards of cardiological fitness. Error, risk and accident causation are introduced in the context of various fatal accidents. In this stimulating and highly informative autobiography, Michael looks back at his time with the ICAO and CAA, drafting cardiological standards for Europe and worldwide travel to spread the message, including the Khyber pass, an aircraft factory in the Indonesian jungle and the slave island of Goree in Senegal. Safety is no accident and history is its judge.
Experimental Investigation Base Pressure On Blunt Trailing Edge Wings At Supersonic Velocities
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Author : Dean R. Chapman
language : en
Publisher:
Release Date : 1952
Experimental Investigation Base Pressure On Blunt Trailing Edge Wings At Supersonic Velocities written by Dean R. Chapman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aerodynamics, Supersonic categories.
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.
Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds
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Author : Gloria Hernandez
language : en
Publisher:
Release Date : 1994
Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds written by Gloria Hernandez and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1994 with Leading edge flaps categories.
Aerodynamic Loads On A Leading Edge Flap And A Leading Edge Slat On The Naca 64a010 Airfoil Section
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Author : John A. Kelly
language : en
Publisher:
Release Date : 1954
Aerodynamic Loads On A Leading Edge Flap And A Leading Edge Slat On The Naca 64a010 Airfoil Section written by John A. Kelly and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aerodynamic load categories.
A previous report, NACA TN 3007, gave force and moment data for the NACA 64A010 airfoil section equipped alternately with a flap and a slat at the leading edge, and with a split flap and a double-slotted flap at the trailing edge. The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA 3007. The pressure data for the leading-edge flap and slat have been converted into coefficients of normal force, chord force, and moment based on the geometry of the leading-edge device.
Pressure Distributions On Two Dimensional Sharp Leading Edge Flat Plates With Sweep Angles Of 0 Degrees 30 Degrees And 45 Degrees At A Mach Number Of 6 And Angles Of Attack From 0 Degrees To 90 Degrees
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Author : James G. Hondros
language : en
Publisher:
Release Date : 1962
Pressure Distributions On Two Dimensional Sharp Leading Edge Flat Plates With Sweep Angles Of 0 Degrees 30 Degrees And 45 Degrees At A Mach Number Of 6 And Angles Of Attack From 0 Degrees To 90 Degrees written by James G. Hondros and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Fluid mechanics categories.
Effects Of Leading Edge Bluntness On Flutter Characteristics Of Some Square Planform Double Wedge Airfoils At A Mach Number Of 15 4
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Author : Robert C. Goetz
language : en
Publisher:
Release Date : 1962
Effects Of Leading Edge Bluntness On Flutter Characteristics Of Some Square Planform Double Wedge Airfoils At A Mach Number Of 15 4 written by Robert C. Goetz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Space vehicles categories.
A Study Of The Asymmetric Transonic Flow Past A Sharp Leading Edge
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Author : Howard A. Stine
language : en
Publisher:
Release Date : 1960
A Study Of The Asymmetric Transonic Flow Past A Sharp Leading Edge written by Howard A. Stine and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerodynamics, Transonic categories.
Summary: An experimental and theoretical study has been made of the two-dimensional transonic flow past a 12° wedge airfoil with lower surface inclined 13° to the air stream. The experimental portion of the study consists of surveys of the flow field about the leading edge in a closed throat tunnel near choking Mach number by means of an X-ray densitometer. From these surveys various features have been determined; namely, the location of the stagnation point, the location of the sonic line, the size of the separation bubble on the upper surface, and the value of the Mach number at the bubble edge. These features were relatively insensitive to changes in Reynolds number in the range from 1X106 to 3X106 based on chord. The theoretical portion of the study consists of the calculation by relaxation methods of an unbounded, inviscid, two-dimensional flow about a portion of the same body at a free-stream Mach number of exactly unity. The calculations yield a separation bubble on the upper surface which has a shape shown to be compatible with known theoretical conditions for viscous attachment to the upper surface of the body. Agreement between theoretically calculated and the experimentally determined features of the flow was good in regions where the local Mach number was 2 or less. In regions of higher local Mach number the agreement was fair. The theoretically determined Mach number on the bubble edge was 2.80 whereas the experimentally determined value was 2.30. The theoretically determined length of the separation bubble was 1.54-percent chord whereas the experimentally determined length was about 5-percent chord. The theoretically determined location of the stagnation point was 0.16-percent chord from the leading edge whereas the experimentally determined location was at 0.56-percent chord. The experience gained in studying the flow suggests the possibility that the solution obtained is not unique and that another solution in better agreement with experiment might exist.
The Proceedings Of The 2018 Asia Pacific International Symposium On Aerospace Technology Apisat 2018
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Author : Xinguo Zhang
language : en
Publisher: Springer
Release Date : 2019-06-08
The Proceedings Of The 2018 Asia Pacific International Symposium On Aerospace Technology Apisat 2018 written by Xinguo Zhang and has been published by Springer this book supported file pdf, txt, epub, kindle and other format this book has been release on 2019-06-08 with Technology & Engineering categories.
This book is a compilation of peer-reviewed papers from the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). The symposium is a common endeavour between the four national aerospace societies in China, Australia, Korea and Japan, namely, the Chinese Society of Aeronautics and Astronautics (CSAA), Royal Aeronautical Society Australian Division (RAeS Australian Division), the Korean Society for Aeronautical and Space Sciences (KSAS) and the Japan Society for Aeronautical and Space Sciences (JSASS). APISAT is an annual event initiated in 2009 to provide an opportunity for researchers and engineers from Asia-Pacific countries to discuss current and future advanced topics in aeronautical and space engineering.
Official Gazette Of The United States Patent Office
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Author : United States. Patent Office
language : en
Publisher:
Release Date : 1959
Official Gazette Of The United States Patent Office written by United States. Patent Office and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Patents categories.
Wind Tunnel And Flight Investigations Of The Use Of Leading Edge Area Suction For The Purpose Of Increasing The Maximum Lift Coefficient Of A 35 Swept Wing Airplane
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Author : Curt A. Holzhauer
language : en
Publisher:
Release Date : 1956
Wind Tunnel And Flight Investigations Of The Use Of Leading Edge Area Suction For The Purpose Of Increasing The Maximum Lift Coefficient Of A 35 Swept Wing Airplane written by Curt A. Holzhauer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aerofoils categories.