An Investigation Of Sting Support Interference On Base Pressure And Forebody Chord Force At Mach Numbers From 0 60 To 1 30
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Facilities And Techniques For Aerodynamic Testing At Transonic Speeds And High Reynolds Number
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Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel
language : en
Publisher:
Release Date : 1971
Facilities And Techniques For Aerodynamic Testing At Transonic Speeds And High Reynolds Number written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Aerodynamics, Transonic categories.
In September 1968, the FDP of AGARD held a specialists' meeting in Paris on transonic aerodynamics, in recognition of the fact that the absence of adequate theoretical methods and wind-tunnels of high enough Reynolds number had already led to costly shortcomings in the transonic performance of certain combat and transport aircraft. Since projected aerospace systems, military, civil and space-oriented, would involve flight at Reynolds number of up to 100 million, the FDP undertook an examination of the requirements of NATO nations for wind tunnel facilities for testing large models at high Reynolds numbers.
An Investigation Of Sting Support Interference On Base Pressure And Forebody Chord Force At Mach Numbers From 0 60 To 1 30
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Author : Phillips J. Tunnell
language : en
Publisher:
Release Date : 1955
An Investigation Of Sting Support Interference On Base Pressure And Forebody Chord Force At Mach Numbers From 0 60 To 1 30 written by Phillips J. Tunnell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with categories.
Sting Interference Effects As Determined By Measurements Of Dynamic Stability Derivatives Surface Pressure And Base Pressure For Mach Numbers 2 Through 8
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Author : Bob L. Uselton
language : en
Publisher:
Release Date : 1980
Sting Interference Effects As Determined By Measurements Of Dynamic Stability Derivatives Surface Pressure And Base Pressure For Mach Numbers 2 Through 8 written by Bob L. Uselton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Hypersonic wind tunnels categories.
Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base.
Effects Of Sting Support Interference On The Base Pressures Of A Model Having A Blunt Nosed Cylinder Body And A Conical Flare At Mach Numbers Of 0 65 To 2 20
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Author :
language : en
Publisher:
Release Date : 1960
Effects Of Sting Support Interference On The Base Pressures Of A Model Having A Blunt Nosed Cylinder Body And A Conical Flare At Mach Numbers Of 0 65 To 2 20 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.
Sting Interference Effects On The Sdm Aircraft As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 3 Through 1 3
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Author : F. B. Cyran
language : en
Publisher:
Release Date : 1980
Sting Interference Effects On The Sdm Aircraft As Determined By Measurements Of Dynamic Stability Derivatives And Base Pressure For Mach Numbers 0 3 Through 1 3 written by F. B. Cyran and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with categories.
An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Critical Sting Length As Determined By The Measurement Of Pitch Damping Derivatives For Laminar Transitional And Turbulent Boundary Layers At Mach Number 3 For Reduced Frequencies Of 0 0033 And 0 0056
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Author : Bob L. Uselton
language : en
Publisher:
Release Date : 1977
Critical Sting Length As Determined By The Measurement Of Pitch Damping Derivatives For Laminar Transitional And Turbulent Boundary Layers At Mach Number 3 For Reduced Frequencies Of 0 0033 And 0 0056 written by Bob L. Uselton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with Pitching (Aerodynamics) categories.
A research program was initiated for the purpose of investigating some of the problem areas in regard to support interference in supersonic wind tunnels. The critical sting length at alpha = 0 was determined by the measurement of pitch-damping derivatives for laminar, transitional, and turbulent boundary layers at the model base. The effect of wedge splitter plates on sting interference was also investigated. By utilizing the small amplitude forced oscillation technique, data were obtained at Mach number 3 on a blunt 7-deg cone for reduced frequencies of 0.0033 and 0.0056. The results showed that the critical sting length with respect to sting interference on pitch-damping data was two model diameters for the two reduced frequencies investigated and was independent of the type of boundary layer at the model base. Decreasing the effective sting length from 3.3 to one model diameter increased the model base pressure substantially and the model surface pressure slightly. The critical sting length for minimal base pressure interference is 2.5 model diameters for this model and these test conditions.
Aristo E Temira E Orfeo Ed Euridice Drammi Per Musica
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Author :
language : en
Publisher:
Release Date : 1776
Aristo E Temira E Orfeo Ed Euridice Drammi Per Musica written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1776 with categories.
Hosmer S Interest And Discount Table
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Author :
language : en
Publisher:
Release Date : 1839*
Hosmer S Interest And Discount Table written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1839* with Interest categories.
Catalogue Of The Renowned Library Formed By Baron Horace De Landau
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Author :
language : en
Publisher:
Release Date : 1949
Catalogue Of The Renowned Library Formed By Baron Horace De Landau 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 categories.
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders
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Author : Colin P. Britcher
language : en
Publisher:
Release Date : 1990
Subsonic Sting Interference On The Aerodynamic Characteristics Of A Family Of Slanted Base Ogive Cylinders written by Colin P. Britcher and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamics categories.