An Investigation of the Role of an Upstream Burst Diaphragm on Flow Quality within a Ludwieg Tube using RANS

Lindörfer, Stefen A.; Anusonti-Inthra, Phuriwat; Combs, Christopher S.; Kreth, Phillip A.; Schmisseur, John D.

doi:10.2514/6.2016-3801

Cited by 6 publications

(1 citation statement)

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“…Numerous supersonic and hypersonic wind tunnel facilities across the world follow a Ludwieg tube design. Cummings and McLaughlin [17] and Lindörfer et al [18] both provided thorough reviews of existing Ludwieg tubes in 2012 and 2016, respectively. Both papers introduce facilities such as the Boeing/AFOSR Quiet Tunnel at Purdue University, a facility capable of Mach 6 flow with a 241 mm (9.5 in.)…”

Section: Introductionmentioning

confidence: 99%

Flow Characterization of the UTSA Hypersonic Ludwieg Tube

et al. 2023

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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 × 106 m−1. 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.

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Section: Introductionmentioning

confidence: 99%