Flow Field Study About A Hemisphere Cylinder In The Transonic And Low Supersonic Mach Number Range
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Flow Field Study About A Hemisphere Cylinder In The Transonic And Low Supersonic Mach Number Range
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Author : T. Hsieh
language : en
Publisher:
Release Date : 1975
Flow Field Study About A Hemisphere Cylinder In The Transonic And Low Supersonic Mach Number Range written by T. Hsieh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamics, Transonic categories.
A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1993
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Aeronautics categories.
Aerodynamic Characteristics Of 2 3 And 4 Caliber Tangent Ogive Cylinders With Nose Bluffness Ratios Of 0 00 0 25 0 50 And 0 75 At Mach Numbers From 0 6 To 4 0
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Author : Carroll B. Butler
language : en
Publisher:
Release Date : 1977
Aerodynamic Characteristics Of 2 3 And 4 Caliber Tangent Ogive Cylinders With Nose Bluffness Ratios Of 0 00 0 25 0 50 And 0 75 At Mach Numbers From 0 6 To 4 0 written by Carroll B. Butler and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with Radomes categories.
This report summarizes wind tunnel test data on various body alone configurations which provide a data matrix for bluff and pointed bodies of revolution with systematic variations in nose bluffness, nose fineness ratio, and cylinder afterbody fineness ratio. Modular model components were used to obtain static stability and drag data, with emphasis on the effect of nose bluffness on drag. Although data is included for tangent ogive noses of fineness ratio 2, 2.25, 2.5, 3.0, and 4, the nose fineness ratios of 2, 3, and 4 calibers include a systematic variation in nose bluffness ratios of 0.00, 0.25, 0.50, and 0.75 on cylindrical midsections of 5, 7, 9, and 11 calibers. A 1-caliber cylindrical afterbody is used with all configurations in this report.
Nasa Technical Paper
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Author :
language : en
Publisher:
Release Date : 1966
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 1966 with Astronautics categories.
A Collection Of Technical Papers
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Author :
language : en
Publisher:
Release Date : 1975
A Collection Of Technical Papers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Fluid dynamics categories.
An Investigation Of Separated Flow About A Hemisphere Cylinder At 0 To 19 Deg Incidence In The Mach Number Range From 0 6 To 1 5
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Author : T. Hsieh
language : en
Publisher:
Release Date : 1976
An Investigation Of Separated Flow About A Hemisphere Cylinder At 0 To 19 Deg Incidence In The Mach Number Range From 0 6 To 1 5 written by T. Hsieh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Aerodynamics, Transonic categories.
The objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg.
Government Reports Announcements Index
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Author :
language : en
Publisher:
Release Date : 1975
Government Reports Announcements Index written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Science categories.
U S Government Research Reports
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Author :
language : en
Publisher:
Release Date : 1964
U S Government Research Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Science categories.
Computational And Numerical Simulations
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Author : Jan Awrejcewicz
language : en
Publisher: BoD – Books on Demand
Release Date : 2014-02-12
Computational And Numerical Simulations written by Jan Awrejcewicz and has been published by BoD – Books on Demand this book supported file pdf, txt, epub, kindle and other format this book has been release on 2014-02-12 with Computers categories.
Computational and Numerical Simulations is an edited book including 20 chapters. Book handles the recent research devoted to numerical simulations of physical and engineering systems. It presents both new theories and their applications, showing bridge between theoretical investigations and possibility to apply them by engineers of different branches of science. Numerical simulations play a key role in both theoretical and application oriented research.
In Flight Transition Measurement On A 100 Cone At Mach Numbers From 0 5 To 2 0
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Author : David F. Fisher
language : en
Publisher:
Release Date : 1982
In Flight Transition Measurement On A 100 Cone At Mach Numbers From 0 5 To 2 0 written by David F. Fisher and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1982 with Boundary layer categories.