Flow Characterization of the UTSA Hypersonic Ludwieg Tube
The characterization of a hypersonic impulse facility is performed using a variety of methods including Pitot probe scans, particle image velocimetry, and schlieren imaging to verify properties such as the velocity, Mach number, wall boundary layer thickness, and freestream turbulence intensity leve...
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-05-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/10/5/463 |
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| author | Eugene N. A. Hoffman Elijah J. LaLonde Angelina Andrade Ivana Chen Hayden A. Bilbo Christopher S. Combs |
| author_facet | Eugene N. A. Hoffman Elijah J. LaLonde Angelina Andrade Ivana Chen Hayden A. Bilbo Christopher S. Combs |
| author_sort | Eugene N. A. Hoffman |
| collection | DOAJ |
| description | The characterization of a hypersonic impulse facility is performed using a variety of methods including Pitot probe scans, particle image velocimetry, and schlieren imaging to verify properties such as the velocity, Mach number, wall boundary layer thickness, and freestream turbulence intensity levels. The experimental results are compared to the numerical simulations of the facility performed with Ansys Fluent to compare the design and operational conditions. The presentation of results in this manuscript is prefaced by a description of the facility and its capabilities. The UTSA Ludwieg tube facility can produce a hypersonic freestream flow with a Mach number of 7.2 ± 0.2 and unit Reynolds numbers of up to 200 × 10<sup>6</sup> m<sup>−1</sup>. The Pitot probe profiles of the 203-mm-square test section indicate a 152 ± 10 mm square freestream core with turbulence intensity values ranging from 1% to 2%. Schlieren imaging of the oblique shockwaves on a 15° wedge model provided an alternate means of verifying the Mach number. Particle image velocimetry and previous molecular tagging velocimetry results showed a good agreement with the Pitot probe data and numerical simulations in the key parameters including freestream velocity, wall boundary layer velocity profiles, and wall boundary layer thickness. |
| first_indexed | 2024-03-11T04:02:42Z |
| format | Article |
| id | doaj.art-70c1d46574e04459a8323134c5f0472f |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-11T04:02:42Z |
| publishDate | 2023-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-70c1d46574e04459a8323134c5f0472f2023-11-18T00:00:38ZengMDPI AGAerospace2226-43102023-05-0110546310.3390/aerospace10050463Flow Characterization of the UTSA Hypersonic Ludwieg TubeEugene N. A. Hoffman0Elijah J. LaLonde1Angelina Andrade2Ivana Chen3Hayden A. Bilbo4Christopher S. Combs5Department of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USADepartment of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USADepartment of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USADepartment of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USADepartment of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USADepartment of Mechanical Engineering, Margie and Bill Klesse College of Engineering and Integrated Design, The University of Texas at San Antonio, San Antonio, TX 78249, USAThe characterization of a hypersonic impulse facility is performed using a variety of methods including Pitot probe scans, particle image velocimetry, and schlieren imaging to verify properties such as the velocity, Mach number, wall boundary layer thickness, and freestream turbulence intensity levels. The experimental results are compared to the numerical simulations of the facility performed with Ansys Fluent to compare the design and operational conditions. The presentation of results in this manuscript is prefaced by a description of the facility and its capabilities. The UTSA Ludwieg tube facility can produce a hypersonic freestream flow with a Mach number of 7.2 ± 0.2 and unit Reynolds numbers of up to 200 × 10<sup>6</sup> m<sup>−1</sup>. The Pitot probe profiles of the 203-mm-square test section indicate a 152 ± 10 mm square freestream core with turbulence intensity values ranging from 1% to 2%. Schlieren imaging of the oblique shockwaves on a 15° wedge model provided an alternate means of verifying the Mach number. Particle image velocimetry and previous molecular tagging velocimetry results showed a good agreement with the Pitot probe data and numerical simulations in the key parameters including freestream velocity, wall boundary layer velocity profiles, and wall boundary layer thickness.https://www.mdpi.com/2226-4310/10/5/463Ludwieg tubewind tunnelhypersonicscharacterizationparticle image velocimetry (PIV) |
| spellingShingle | Eugene N. A. Hoffman Elijah J. LaLonde Angelina Andrade Ivana Chen Hayden A. Bilbo Christopher S. Combs Flow Characterization of the UTSA Hypersonic Ludwieg Tube Aerospace Ludwieg tube wind tunnel hypersonics characterization particle image velocimetry (PIV) |
| title | Flow Characterization of the UTSA Hypersonic Ludwieg Tube |
| title_full | Flow Characterization of the UTSA Hypersonic Ludwieg Tube |
| title_fullStr | Flow Characterization of the UTSA Hypersonic Ludwieg Tube |
| title_full_unstemmed | Flow Characterization of the UTSA Hypersonic Ludwieg Tube |
| title_short | Flow Characterization of the UTSA Hypersonic Ludwieg Tube |
| title_sort | flow characterization of the utsa hypersonic ludwieg tube |
| topic | Ludwieg tube wind tunnel hypersonics characterization particle image velocimetry (PIV) |
| url | https://www.mdpi.com/2226-4310/10/5/463 |
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