Aerodynamics Of The Model Airplane Airfoil Measurements
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Aerodynamics Of The Model Airplane Airfoil Measurements
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Author : Franz Wilhelm Schmitz
language : en
Publisher:
Release Date : 1967
Aerodynamics Of The Model Airplane Airfoil Measurements written by Franz Wilhelm Schmitz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Aerodynamics categories.
Aerodynamics Of The Model Airplane
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Author : F. W. Schmitz
language : de
Publisher:
Release Date : 1942*
Aerodynamics Of The Model Airplane written by F. W. Schmitz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1942* with Aerofoils categories.
Aerodynamics Of The Model Airplane Part 1 Airfoil Measurements
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Author :
language : en
Publisher:
Release Date : 1967
Aerodynamics Of The Model Airplane Part 1 Airfoil Measurements written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with categories.
Model Aircraft Aerodynamics
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Author : Martin Simons
language : en
Publisher: Chris Lloyd Sales & Marketing
Release Date : 2015-01-15
Model Aircraft Aerodynamics written by Martin Simons and has been published by Chris Lloyd Sales & Marketing this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-01-15 with Technology & Engineering categories.
This is the latest edition - fully revised and updated - of the standard textbook on aerodynamic theory, as applied to model flight. Everything is explained in a concise and practical form for those enthusiasts who appreciate that a better understanding of model behaviour is the sure path to greater success and enjoyment, whether just for fun or in competition. The revisions for this new edition reflect the significant developments in model aircraft during the last few years, and include brand new data: * The chapter on aerofoils has been rewritten to take account of the vast amount of testing carried out recently in the USA by the University of Illinois. * A brand new chapter explains the latest research into the flight of birds and insects and how it is applied to small drones and model-sized surveillance aircraft. * Older wind tunnel test reports all replaced with the latest trials and measurements.
Aerodynamic Characteristics Temperature And Noise Measurements Of A Large Scale External Flow Jet Augmented Flap Model With Turbojet Engines Operating
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Author : Marvin P. Fink
language : en
Publisher:
Release Date : 1961
Aerodynamic Characteristics Temperature And Noise Measurements Of A Large Scale External Flow Jet Augmented Flap Model With Turbojet Engines Operating written by Marvin P. Fink and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Compressed air categories.
An investigation has been conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35° sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 65(1)-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with half-span and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range or angles of attack from -8° to 16° for Reynolds numbers from 1.8 x 106 to 4.4 x 106 and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hot-jet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Skin temperatures were about 340° F and wing heating could be handled with available materials without cooling. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane.
Measurements And Analysis Of The Motion Of A Canard Airplane Model In Gusts
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Author : Philip Donely
language : en
Publisher:
Release Date : 1940
Measurements And Analysis Of The Motion Of A Canard Airplane Model In Gusts written by Philip Donely and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1940 with Airplanes categories.
A model of a hypothetical canard airplane, which was designed to be of the same size and general aerodynamic characteristics as a Boeing B-247 airplane, was tested in the N.A.C.A. gust tunnel at one wing loading, one forward speed, one gust velocity, and three gust gradients. The purpose of these tests was to determine the reactions of the model and to compare them with the results of unpublished tests on an equivalent model of the Boeing B-247 airplane.
Comparison Of Measured And Predicted Indicated Angles Of Attack Near The Fuselages Of A Triangular Wing Wind Tunnel Model And A Swept Wing Fighter Airplane In Flight
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Author : Norman M. McFadden
language : en
Publisher:
Release Date : 1953
Comparison Of Measured And Predicted Indicated Angles Of Attack Near The Fuselages Of A Triangular Wing Wind Tunnel Model And A Swept Wing Fighter Airplane In Flight written by Norman M. McFadden 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.
Abstract: Comparisons are presented of predicted values of flow angles and those measured using detectors close to the surface of the forward portion of fuselages of a large-scale, triangular-wing, wind-tunnel model at low speeds and a 35° swept-wing fighter airplane in flight. Effects of flap deflection on the upwash of the triangular-wing model are included.
Basic Pressure Measurements On A 0 0667 Scale Model Of The North American X 15 Research Airplane At Transonic Speeds
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Author :
language : en
Publisher:
Release Date : 1960
Basic Pressure Measurements On A 0 0667 Scale Model Of The North American X 15 Research Airplane At Transonic Speeds written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.
High Speed Problems Of Aircraft And Experimental Methods
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Author : Allen F. Donovan
language : en
Publisher: Princeton University Press
Release Date : 2015-12-08
High Speed Problems Of Aircraft And Experimental Methods written by Allen F. Donovan and has been published by Princeton University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-12-08 with Science categories.
Volume VIII of the High Speed Aerodynamics and Jet Propulsion series. This volume includes: performance calculation at high speed; stability and control of high speed aircraft; aeroelasticity and flutter; model testing; transonic wind tunnels; supersonic tunnels; hypersonic experimental facilities; low density wind tunnels; shock tube; wind tunnel measurements; instrumented models in free flight; piloted aircraft testing; free flight range methods. Originally published in 1961. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Ice Accretions And Icing Effects For Modern Airfoils
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Author : Harold E. Addy
language : en
Publisher:
Release Date : 2000
Ice Accretions And Icing Effects For Modern Airfoils written by Harold E. Addy and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with Aerofoils categories.
Icing tests were conducted to document ice shapes formed on three different two-dimensional airfoils and to study the effects of the accreted ice on aerodynamic performance. The models tested were representative of airfoil designs in current use for each of the commercial transport, business jet, and general aviation categories of aircraft. The models were subjected to a range of icing conditions in an icing wind tunnel. The conditions were selected primarily from the Federal Aviation Administration's Federal Aviation Regulations 25 Appendix C atmospheric icing conditions. A few large droplet icing conditions were included. To verify the aerodynamic performance measurements, molds were made of selected ice shapes formed in the icing tunnel. Castings of the ice were made from the molds and placed on a model in a dry, low-turbulence wind tunnel where precision aerodynamic performance measurements were made. Documentation of all the ice shapes and the aerodynamic performance measurements made during the icing tunnel tests is included in this report. Results from the dry, low-turbulence wind tunnel tests are also presented.