{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2026,4,9]],"date-time":"2026-04-09T05:10:53Z","timestamp":1775711453628,"version":"3.50.1"},"reference-count":104,"publisher":"MDPI AG","issue":"15","license":[{"start":{"date-parts":[[2021,7,28]],"date-time":"2021-07-28T00:00:00Z","timestamp":1627430400000},"content-version":"vor","delay-in-days":0,"URL":"https:\/\/creativecommons.org\/licenses\/by\/4.0\/"}],"content-domain":{"domain":[],"crossmark-restriction":false},"short-container-title":["Sensors"],"abstract":"<jats:p>In this contribution, three methodologies based on temperature-sensitive paint (TSP) data were further developed and applied for the optical determination of the critical locations of flow separation and reattachment in compressible, high Reynolds number flows. The methodologies rely on skin-friction extraction approaches developed for low-speed flows, which were adapted in this work to study flow separation and reattachment in the presence of shock-wave\/boundary-layer interaction. In a first approach, skin-friction topological maps were obtained from time-averaged surface temperature distributions, thus enabling the identification of the critical lines as converging and diverging skin-friction lines. In the other two approaches, the critical lines were identified from the maps of the propagation celerity of temperature perturbations, which were determined from time-resolved TSP data. The experiments were conducted at a freestream Mach number of 0.72 and a chord Reynolds number of 9.7 million in the Transonic Wind Tunnel G\u00f6ttingen on a VA-2 supercritical airfoil model, which was equipped with two exchangeable TSP modules specifically designed for transonic, high Reynolds number tests. The separation and reattachment lines identified via the three different TSP-based approaches were shown to be in mutual agreement, and were also found to be in agreement with reference experimental and numerical data.<\/jats:p>","DOI":"10.3390\/s21155106","type":"journal-article","created":{"date-parts":[[2021,7,28]],"date-time":"2021-07-28T21:21:04Z","timestamp":1627507264000},"page":"5106","update-policy":"https:\/\/doi.org\/10.3390\/mdpi_crossmark_policy","source":"Crossref","is-referenced-by-count":6,"title":["Skin-Friction-Based Identification of the Critical Lines in a Transonic, High Reynolds Number Flow via Temperature-Sensitive Paint"],"prefix":"10.3390","volume":"21","author":[{"ORCID":"https:\/\/orcid.org\/0000-0003-0642-0199","authenticated-orcid":false,"given":"Marco","family":"Costantini","sequence":"first","affiliation":[{"name":"German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Bunsenstrasse 10, D-37073 G\u00f6ttingen, Germany"}]},{"given":"Ulrich","family":"Henne","sequence":"additional","affiliation":[{"name":"German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Bunsenstrasse 10, D-37073 G\u00f6ttingen, Germany"}]},{"ORCID":"https:\/\/orcid.org\/0000-0001-7592-6922","authenticated-orcid":false,"given":"Christian","family":"Klein","sequence":"additional","affiliation":[{"name":"German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Bunsenstrasse 10, D-37073 G\u00f6ttingen, Germany"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-6733-078X","authenticated-orcid":false,"given":"Massimo","family":"Miozzi","sequence":"additional","affiliation":[{"name":"National Research Council (CNR), Institute of Marine Engineering, Via di Vallerano 139, I-00128 Rome, Italy"}]}],"member":"1968","published-online":{"date-parts":[[2021,7,28]]},"reference":[{"key":"ref_1","doi-asserted-by":"crossref","unstructured":"Lynde, M.N., and Campbell, R.L. 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