Weiss, Armin und Gardner, Anthony und Klein, Christian und Raffel, Markus (2017) Boundary-layer transition measurements on Mach-scaled helicopter rotor blades in climb. CEAS Aeronautical Journal, 8, Seiten 613-623. Springer. doi: 10.1007/s13272-017-0263-2. ISSN 1869-5590.
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Offizielle URL: http://link.springer.com/article/10.1007/s13272-017-0263-2
Kurzfassung
In this work laminar-turbulent boundary-layer transition is investigated on the suction side of Mach-scaled helicopter rotor blades in climb. The phenomenon is assessed by means of temperature-sensitive paint (TSP). Results are compared to a data sample acquired by infrared (IR) thermography and accompanied by integral thrust-and local surface pressure measurements at two radial blade sections. Spatially high resolved data allow for precise detection of boundary-layer transition along the outer 60 % of the blade span. Results obtained via TSP and IR show remarkable agreement with minor deviations due to different surface qualities of the respective blades tested. TSP data are obtained at various collective pitch angles and three different rotating speeds corresponding to chord Reynolds-and Mach numbers based on blade tip speed of Retip = 4.8-9.31x105 and Mtip = 0.29-0.57, respectively. The transition position is detected with an accuracy of better than 1% chord and the findings show overall coherence as blade loading and tip chord Reynolds number are varied. Experimental findings are shown tobe consistent with two-dimensional simulations using the eN-envelope method for transition prediction. Based on quantitative agreement between measured and calculated surface pressures, a comparison of the corresponding transition results suggests a critical amplification factor of Ncr. = 5.5 best suited for transition prediction in the rotating test facility of the DLR Göttingen.
elib-URL des Eintrags: | https://elib.dlr.de/116938/ | ||||||||||||||||||||
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Dokumentart: | Zeitschriftenbeitrag | ||||||||||||||||||||
Zusätzliche Informationen: | Volume 8, Issue 4; Published online: 19 September 2017 | ||||||||||||||||||||
Titel: | Boundary-layer transition measurements on Mach-scaled helicopter rotor blades in climb | ||||||||||||||||||||
Autoren: |
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Datum: | 19 September 2017 | ||||||||||||||||||||
Erschienen in: | CEAS Aeronautical Journal | ||||||||||||||||||||
Referierte Publikation: | Ja | ||||||||||||||||||||
Open Access: | Ja | ||||||||||||||||||||
Gold Open Access: | Nein | ||||||||||||||||||||
In SCOPUS: | Ja | ||||||||||||||||||||
In ISI Web of Science: | Nein | ||||||||||||||||||||
Band: | 8 | ||||||||||||||||||||
DOI: | 10.1007/s13272-017-0263-2 | ||||||||||||||||||||
Seitenbereich: | Seiten 613-623 | ||||||||||||||||||||
Herausgeber: |
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Verlag: | Springer | ||||||||||||||||||||
ISSN: | 1869-5590 | ||||||||||||||||||||
Status: | veröffentlicht | ||||||||||||||||||||
Stichwörter: | boundary-layer transition, helicopter roter blades, temperature-sensitive paint, infrared thermography, eAN-method | ||||||||||||||||||||
HGF - Forschungsbereich: | Luftfahrt, Raumfahrt und Verkehr | ||||||||||||||||||||
HGF - Programm: | Luftfahrt | ||||||||||||||||||||
HGF - Programmthema: | Flugzeuge | ||||||||||||||||||||
DLR - Schwerpunkt: | Luftfahrt | ||||||||||||||||||||
DLR - Forschungsgebiet: | L AR - Aircraft Research | ||||||||||||||||||||
DLR - Teilgebiet (Projekt, Vorhaben): | L - Simulation und Validierung (alt) | ||||||||||||||||||||
Standort: | Göttingen | ||||||||||||||||||||
Institute & Einrichtungen: | Institut für Aerodynamik und Strömungstechnik > Experimentelle Verfahren, GO Institut für Aerodynamik und Strömungstechnik > Hubschrauber, GO | ||||||||||||||||||||
Hinterlegt von: | Bachmann, Barbara | ||||||||||||||||||||
Hinterlegt am: | 13 Dez 2017 14:37 | ||||||||||||||||||||
Letzte Änderung: | 21 Nov 2023 09:37 |
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