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Designing a Shock Tunnel to Enable H...

Peddada, Sumukh,

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Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows /

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows // Sumukh Peddada.
作者:	Peddada, Sumukh,
面頁冊數:	1 electronic resource (53 pages)
附註:	Source: Masters Abstracts International, Volume: 86-01.
Contained By:	Masters Abstracts International86-01.
標題:	Fluid mechanics. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31328527
ISBN:	9798383226261

Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows /
Peddada, Sumukh,

Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows /Sumukh Peddada. - 1 electronic resource (53 pages)

Source: Masters Abstracts International, Volume: 86-01.

This study presents the design and analysis of a shock tunnel facility, utilizing existing high-pressure pipes within the UWAA department. The research aims to elucidate the trade-offs between Reynolds number, enthalpy, and test time across a range of configurations. The methodology involves using the WISTL shock tube code from the University of Wisconsin, integrated with an in-house nozzle solving code to design and model a reflected shock tunnel. The setup features a driver length of 12 ft and a driven length of 56 ft with a diameter of 7 in, achieving steady-state test durations ranging from 3 to 16 ms. This configuration enables exploration of Reynolds numbers from 106 - 108 m−1 and enthalpy conditions from 0.3 - 1.6 MJ/kg. A comparative analysis with a Ludweig tube configuration, using the same pipe sections, demonstrates the shock tunnel's capability to handle high enthalpy at higher Mach numbers without issues, offering greater flexibility. The results reveal stable stagnation conditions with minimal pressure and temperature fluctuation with changes in length but high sensitivity to driver and driven pressures. A Mach Number in the range 6 - 8 with the current test section size of 0.3m is identified as striking a reasonable balance between various parameters. In conclusion, the designed shock tunnel facility demonstrates remarkable flexibility and robust performance over test conditions and showcasing its potential for advancing research in hypersonic flow.

English

ISBN: 9798383226261Subjects--Topical Terms:

528155
Fluid mechanics.
Subjects--Index Terms:

Shock tunnel facility

Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows /
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245 1 0 $a Designing a Shock Tunnel to Enable High Enthalpy Experimental Investigation of Hypersonic Flows / $c Sumukh Peddada.
264 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2024
300 $a 1 electronic resource (53 pages)
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500 $a Source: Masters Abstracts International, Volume: 86-01.
500 $a Advisors: Williams, Owen J. H.; Knowlen, Carl.
502 $b Master's $c University of Washington $d 2024.
520 $a This study presents the design and analysis of a shock tunnel facility, utilizing existing high-pressure pipes within the UWAA department. The research aims to elucidate the trade-offs between Reynolds number, enthalpy, and test time across a range of configurations. The methodology involves using the WISTL shock tube code from the University of Wisconsin, integrated with an in-house nozzle solving code to design and model a reflected shock tunnel. The setup features a driver length of 12 ft and a driven length of 56 ft with a diameter of 7 in, achieving steady-state test durations ranging from 3 to 16 ms. This configuration enables exploration of Reynolds numbers from 106 - 108 m−1 and enthalpy conditions from 0.3 - 1.6 MJ/kg. A comparative analysis with a Ludweig tube configuration, using the same pipe sections, demonstrates the shock tunnel's capability to handle high enthalpy at higher Mach numbers without issues, offering greater flexibility. The results reveal stable stagnation conditions with minimal pressure and temperature fluctuation with changes in length but high sensitivity to driver and driven pressures. A Mach Number in the range 6 - 8 with the current test section size of 0.3m is identified as striking a reasonable balance between various parameters. In conclusion, the designed shock tunnel facility demonstrates remarkable flexibility and robust performance over test conditions and showcasing its potential for advancing research in hypersonic flow.
546 $a English
590 $a School code: 0250
650 4 $a Fluid mechanics. $3 528155
650 4 $a Aeronomy. $3 2102064
650 4 $a Aerospace engineering. $3 1002622
653 $a Shock tunnel facility
653 $a High-pressure pipes
653 $a Ludweig tube configuration
653 $a Hypersonic flow
690 $a 0204
690 $a 0367
690 $a 0538
710 2 $a University of Washington. $b Aeronautics and Astronautics. $e degree granting institution. $3 3829956
720 1 $a Williams, Owen J. H. $e degree supervisor.
720 1 $a Knowlen, Carl $e degree supervisor.
773 0 $t Masters Abstracts International $g 86-01.
790 $a 0250
791 $a Master's
792 $a 2024
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31328527