Flow Characteristics of the Ballistic Research Laboratories' Supersonic Wind Tunnel PDF Download
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Author: Clarence C. Bush
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
The Ballistic Research Laboratories' Supersonic Wind Tunnel No. 1 flow characteristics are presented in detail to assist those who may wish to make use of the facility. Techniques and instrumentation used i calibrating supersonic nozzles for Mach number and flow direction distributions are discussed, as well as nozzle adjustment procedures used to improve the flow in the tsting region for nozzles with flexible walls. (Author).
Author: Clarence C. Bush
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
The Ballistic Research Laboratories' Supersonic Wind Tunnel No. 1 flow characteristics are presented in detail to assist those who may wish to make use of the facility. Techniques and instrumentation used i calibrating supersonic nozzles for Mach number and flow direction distributions are discussed, as well as nozzle adjustment procedures used to improve the flow in the tsting region for nozzles with flexible walls. (Author).
Author:
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Category : Supersonic wind tunnels
Languages : en
Pages : 36
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Author:
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ISBN:
Category :
Languages : en
Pages : 504
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Author:
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Category : Aeronautics
Languages : en
Pages : 972
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Author: Alan. L. Kistler
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ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 62
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Author:
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ISBN:
Category :
Languages : en
Pages : 44
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The boundaries for the onset of air liquefaction were experimentally determined. These boundaries indicate the regions where the liquefaction of air constituents has an effect on the flow properties in the test section. The boundaries were determined by making static and total head pressure measurements (with varying temperature) throughout the appropriate Mach and Reynolds number ranges of both the supersonic and hypersonic wind tunnels. The results show that air liquefaction occurs near the theoretical boundary (Clausius-Clapeyron) for Mach numbers 4.75 and 5.00 with little, if any, supersaturation. However, as the Mach number increases to 6.0, 7.5 and 9.2, there is an increase in the amount of supersaturation before liquefaction occurs, and at a given Mach number, the difference between the experimental and theoretical temperature at the onset of liquefaction is about the same at all pressure levels tested. These results may allow a relaxation of our stagnation temperature requirements by an amount which would be of considerable operational significance at M = 9.2.
Author:
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Category : Science
Languages : en
Pages : 500
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 776
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Author:
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Category : Government publications
Languages : en
Pages : 1016
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 1416
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