Test Time In Low Pressure Shock Tubes
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Test Time In Low Pressure Shock Tubes
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Author : Aerospace Corporation
language : en
Publisher:
Release Date : 1962
Test Time In Low Pressure Shock Tubes written by Aerospace Corporation and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Shock tubes categories.
Shock Tube Test Time Limitation Due To Turbulent Wall Boundary Layer
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Author : Aerospace Corporation
language : en
Publisher:
Release Date : 1963
Shock Tube Test Time Limitation Due To Turbulent Wall Boundary Layer written by Aerospace Corporation and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Boundary layer categories.
Shock tube test time limitation due to the premature arrival of the contact surface is analytically investigated for wholly turbulent wall boundary layers. The results are compared with those for wholly laminar wall boundary layers. Working curves are presented for more accurate estimates of test time in specific cases. (Author) -- NTRL website.
Strategies For Obtaining Long Constant Pressure Test Times In Shock Tubes
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Author :
language : en
Publisher:
Release Date : 2015
Strategies For Obtaining Long Constant Pressure Test Times In Shock Tubes written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015 with categories.
Several techniques have been developed for obtaining long, constant-pressure test times in reflected shock wave experiments in a shock tube, including the use of driver inserts, driver gas tailoring, helium gas diaphragm interfaces, driver extensions, and staged driver gas filling. Here, we detail these techniques, including discussion on the most recent strategy, staged driver gas filling. Experiments indicate that this staged filling strategy increases available test time by roughly 20 % relative to single-stage filling of tailored driver gas mixtures, while simultaneously reducing the helium required per shock by up to 85 %. This filling scheme involves firstly mixing a tailored helium-nitrogen mixture in the driver section as in conventional driver filling and, secondly, backfilling a low-speed-of-sound gas such as nitrogen or carbon dioxide from a port close to the end cap of the driver section. Using this staged driver gas filling, in addition to the other techniques listed above, post-reflected shock test times of up to 0.102 s (102 ms) at 524 K and 1.6 atm have been obtained. Spectroscopically based temperature measurements in non-reactive mixtures have confirmed that temperature and pressure conditions remain constant throughout the length of these long test duration trials. Finally, these strategies have been used to measure low-temperature n-heptane ignition delay times.
Analysis Of Test Times And Boundary Layer Induced Property Variations In A Circular Shock Tube
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Author : John J. Bertin
language : en
Publisher:
Release Date : 1967
Analysis Of Test Times And Boundary Layer Induced Property Variations In A Circular Shock Tube written by John J. Bertin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Boundary layer categories.
On Flow Duration In Low Pressure Shock Tubes
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Author : Anatol Roshko
language : en
Publisher:
Release Date : 1960
On Flow Duration In Low Pressure Shock Tubes written by Anatol Roshko 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.
Measurements Of Flow Duration In A Low Pressure Shock Tube
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Author : Virgil A. Sandborn
language : en
Publisher:
Release Date : 1962
Measurements Of Flow Duration In A Low Pressure Shock Tube written by Virgil A. Sandborn and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.
Shock Tube And Gas Dynamic Design Considerations And Implementation For Extended Test Times
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Author : Jacklyn Higgs
language : en
Publisher:
Release Date : 2022
Shock Tube And Gas Dynamic Design Considerations And Implementation For Extended Test Times written by Jacklyn Higgs and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2022 with categories.
A new shock tube test section has been designed and manufactured for the purpose of increasing the test time and expanding the applications of the shock tube for a multitude of ongoing and future projects. One purpose for the test section extension is to allow for flow visualization of droplets impacted by a shock wave for the interaction of hypersonic vehicles and atmospheric disturbances. Another purpose is to measure behind the incident shock to capture the chemical kinetics for a high-altitude environment and low-pressure, high-temperature space applications. This new test section contains 24 round optical ports for laser spectroscopy for multiple measurement locations in addition to 3 rectangular ports upstream for introducing and imaging droplets in the tube. StanShock was used to simulate the expected test time for the desired temperatures and pressures. This was compared against theoretical calculations of test time as a function of distance and velocity of the shock. The optimal length of the extension of 5 feet was then determined based on minimum required test time and limitations of the physical lab space.
Flow Nonuniformity In Shock Tubes Operating At Maximum Test Time
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Author : H. Mirels
language : en
Publisher:
Release Date : 1966
Flow Nonuniformity In Shock Tubes Operating At Maximum Test Time written by H. Mirels and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with categories.
Shock tube flow nonuniformity is investigated in the limit where the shock and contact surface have reached their maximum separation. Ideal gases are considered. It is found that all fluid properties increase in value between the shock and contact surface. The nonuniformity is greatest when gamma (ratio of specific heats) is large and M sub s (shock Mach number) is low. For gamma = 5/3 and M sub s> or = 3, the static temperature, density, and pressure increase by about 8, 12 and 20%, respectively; the stagnation temperature increases by about 35%, and the stagnation pressure, dynamic pressure, and stagnation point heat transfer increase by about a factor of 2. These results apply to turbulent as well as laminar boundary layers. The variation of flow properties with distance behind the shock, as well as particle time of flight, is given for both wholly laminar and wholly turbulent wall boundary layers. These results are particularly important for chemical rate and heat transfer studies. (Author).
Measurement Of Flow Duration In A Low Pressure Shock Tube
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Author : Virgil A. Sandborn
language : en
Publisher:
Release Date : 1962
Measurement Of Flow Duration In A Low Pressure Shock Tube written by Virgil A. Sandborn and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.
Measurement Of Frequency Response Of Pressure Gauges By A High Pressure Shock Tube Technique
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Author : S. P. Pfaff
language : en
Publisher:
Release Date : 1958
Measurement Of Frequency Response Of Pressure Gauges By A High Pressure Shock Tube Technique written by S. P. Pfaff and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Shock tubes categories.
