Studies Of The Use Of Freon 12 As A Wind Tunnel Testing Medium
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Studies Of The Use Of Freon 12 As A Wind Tunnel Testing Medium
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Author : Albert E. Von Doenhoff
language : en
Publisher:
Release Date : 1953
Studies Of The Use Of Freon 12 As A Wind Tunnel Testing Medium written by Albert E. Von Doenhoff and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Dichlorodifluoromethane categories.
A number of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing have been made. The use of Freon-12 instead of air makes possible large savings in wind-tunnel drive power. Because of the fact that the ratio of specific heats is approximately 1.13 for Freon-12 as compared with 1.4 for air, some differences exist between data obtained in Freon-12 and air. Methods for predicting aerodynamic characteristics of bodies in air from data obtained in Freon-12, however, have been developed from the concept of similarity of the streamline pattern. These methods, derived from consideration of two-dimensional flows, provide substantial agreement in all cases for which comparative data are available. These data consist of measurements throughout a range of Mach number from approximately 0.4 to 1.2 of pressure distributions and hinge moments on swept and unswept wings having aspect ratios ranging from 4.0 to 9.0, including cases where a substantial part of the wing was stalled.
Technical Note National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1953
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 1953 with Aeronautics categories.
Nasa Technical Note
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Author :
language : en
Publisher:
Release Date : 1976
Nasa 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 1976 with categories.
Research Abstracts
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1951
Research Abstracts 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.
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.
Nasa Technical Paper
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Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 1991
Nasa Technical Paper written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aeronautics categories.
Nasa Technical Paper
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Author :
language : en
Publisher:
Release Date : 1991
Nasa Technical Paper written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Astronautics categories.
Flutter Studies To Determine Nacelle Aerodynamic Effects On A Fan Jet Transport Model For Two Mount Systems And Two Wind Tunnels
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Author : Moses G. Farmer
language : en
Publisher:
Release Date : 1970
Flutter Studies To Determine Nacelle Aerodynamic Effects On A Fan Jet Transport Model For Two Mount Systems And Two Wind Tunnels written by Moses G. Farmer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1970 with Aerodynamics categories.
Low-speed flutter studies of a dynamically and elastically scaled model of a large multijet transport airplane have been conducted primarily to determine the nacelle aerodynamic effects for high-bypass-ratio fan-jet engines. Data were obtained on a vertical rod mount in two wind tunnels and on a two-cable mount in one of the tunnels. The flutter response of the model was found to be dependent on nacelle aerodynamics, engine-pylon stiffness, mount-system-wind-tunnel configuration, and mass ratio.
Nuclear Science Abstracts
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Author :
language : en
Publisher:
Release Date : 1953
Nuclear Science Abstracts 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 Nuclear energy categories.
Wind Tunnel Evaluation Of A Model Helicopter Main Rotor Blade With Slotted Airfoils At The Tip
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Author :
language : en
Publisher:
Release Date : 2001
Wind Tunnel Evaluation Of A Model Helicopter Main Rotor Blade With Slotted Airfoils At The Tip written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with categories.
Data for rotors using unconventional airfoils are of interest to permit an evaluation of this technology's capability to meet the U.S. Army's need for increased helicopter mission effectiveness and improved safety and survivability. Thus, an experimental investigation was conducted in the Langley Transonic Dynamics Tunnel (TDT) to evaluate the effect of using slotted airfoils in the rotor blade tip region (85 to 100 percent radius) on rotor aerodynamic performance and loads. Four rotor configurations were tested in forward flight at advance ratios from 0.15 to 0.45 and in hover in-ground effect. The hover tip Mach number was 0.627, which is representative of a design point of 4000-ft geometric altitude and a temperature of 95 degrees F. The baseline rotor configuration had a conventional single element airfoil in the tip region. A second rotor configuration had a forward-slotted airfoil with a -6 degrees slat, a third configuration had a forward-slotted airfoil with a -10 degrees slat, and a fourth configuration had an aft-slotted airfoil with a 3 degrees flap (trailing edge down). The results of this investigation indicate that the -6 degrees slat configuration offers some performance and loads benefits over the other three configurations.