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Shockwave boundary layer interaction of laminar/transitional flow past a sharp fin

Ecker, Tobias und Martinez Schramm, Jan und Schmidt, Leni und Surujhlal, Divek und Wagner, Alexander (2022) Shockwave boundary layer interaction of laminar/transitional flow past a sharp fin. In: 2nd International Conference on High-Speed Vehicle Science & Technology HiSST 2022, Seiten 1-13. CEAS. 2nd International Conference on High-Speed Vehicle Science & Technology HiSST 2022, 2022-09-11 - 2022-09-15, Brügge, Belgien.

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Offizielle URL: https://atpi.eventsair.com/QuickEventWebsitePortal/hisst-2020/website

Kurzfassung

Ever since NASA’s X-plane program had developed demonstrators (X-15) pushing into the hypersonic high altitude flight regimes, the effects of shock impingement and interference on local aerodynamic heating have been a key issue for the design of hypersonic flight concepts. Currently DLR is involved in several flight experiments, one of which is STORT which focuses on aerothermal loads on hot structures. One essential structure flown on the STORT flight experiment is the fins experiment on the third stage. The fins were investigated both on the vehicle, in windtunnels in Cologne and Göttingen but also numerically. For the windtunnel experiment in the HEG (High Enthalpy Shock Tunnel Göttingen) the object of investigation is a plate mounted fin which scales 1:2 to the flight hardware. The fin-induced shock boundary layer interaction (SWBLI) on the plate leads to increased thermal loads. The heat flux on the flat plate and fin are investigated using temperature sensitive paints (TSP). For the current study the flow on the plate and around the fin is studied for two HEG freestream conditions at Mach 7.4 using RANS CFD. CFD calculations at both 0 deg AoF and 15 deg AoF were performed and compared for flow topology and turbulence model influence. For 2 configurations first preliminary comparisons between experimental and CFD data were conducted. While the XIII freestream condition compares well between experiment and CFD, the XV freestream condition which shows clear signs of transitional flow exhibits rather complex physical phenomena which requirevfurther investigation, both experimentally and numerically.

elib-URL des Eintrags:https://elib.dlr.de/188440/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Shockwave boundary layer interaction of laminar/transitional flow past a sharp fin
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Ecker, TobiasTobias.Ecker (at) dlr.dehttps://orcid.org/0000-0001-7134-1185NICHT SPEZIFIZIERT
Martinez Schramm, JanJan.Martinez (at) dlr.dehttps://orcid.org/0000-0002-8891-6253NICHT SPEZIFIZIERT
Schmidt, LeniLeni.Schmidt (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Surujhlal, DivekDivek.Surujhlal (at) dlr.dehttps://orcid.org/0000-0002-0349-3328NICHT SPEZIFIZIERT
Wagner, AlexanderAlexander.Wagner (at) dlr.dehttps://orcid.org/0000-0002-9700-1522NICHT SPEZIFIZIERT
Datum:11 September 2022
Erschienen in:2nd International Conference on High-Speed Vehicle Science & Technology HiSST 2022
Referierte Publikation:Ja
Open Access:Ja
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Seitenbereich:Seiten 1-13
Verlag:CEAS
Status:veröffentlicht
Stichwörter:SWBLI, shock, fin, heat flux, CFD
Veranstaltungstitel:2nd International Conference on High-Speed Vehicle Science & Technology HiSST 2022
Veranstaltungsort:Brügge, Belgien
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:11 September 2022
Veranstaltungsende:15 September 2022
Veranstalter :ESA
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Schlüsseltechnologien für hochenergetische Rückkehrflüge der Trägerstufen (STORT)
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge, GO
Hinterlegt von: Ecker, Tobias
Hinterlegt am:21 Okt 2022 18:25
Letzte Änderung:24 Apr 2024 20:49

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