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Boundary Layer Transition Studies on the HEXAFLY-INT Hypersonic Glide Vehicle

Wagner, Alexander and Martinez Schramm, Jan and Wartemann, Viola and Ponchio Camillo, Giannino and Ozawa, Hiroshi and Steelant, Johan (2019) Boundary Layer Transition Studies on the HEXAFLY-INT Hypersonic Glide Vehicle. FAR 2019 - International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering, 2019-09-30 - 2019-10-03, Monopoli, Italien.

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Official URL: https://atpi.eventsair.com/QuickEventWebsitePortal/far2019/website


The present experimental study addresses natural boundary layer transition and the effect of surface imperfections such as steps and gaps on the boundary layer state of the HEXAFLY-INT hypersonic glider. An experimental test campaign using a 1:2.6 scaled model was carried out in the High Enthalpy Shock Tunnel Gottingen (HEG) at Mach 7.4. The artificial steps and gaps on the surface are generated by means of e.g. adjustable leading edge segments which are precise scaled down elements of the flight vehicle segments. The purpose of the study is to reproduce unavoidable surface imperfections caused for instance by different thermal expansion at material junctions during flight. Furthermore, the study aims to extend the roughness induced transition database on complex flight vehicle geometries. The experimental study at HEG was carried out using surface mounted transducers to determine the pressure distribution and the surface heat flux density on the windward side of the glide vehicle. Furthermore, temperature sensitive paint was used to get quantitative information on the flow topology around the glider. The techniques essentially helped revealing the existence of a vortex pair which after breaking down forms turbulent wedges. Until the experimental tests in HEG the existence of the vortex pair was unknown. This led to a revision of the thermal boundary conditions for the HEXAFLY-INT glider thermal analysis since the surface heat flux density in the area wetted by the turbulent wedges was found to locally increase up to five times above the laminar heat flux level.

Item URL in elib:https://elib.dlr.de/130117/
Document Type:Conference or Workshop Item (Speech)
Title:Boundary Layer Transition Studies on the HEXAFLY-INT Hypersonic Glide Vehicle
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Wagner, AlexanderDLRhttps://orcid.org/0000-0002-9700-1522UNSPECIFIED
Wartemann, ViolaUNSPECIFIEDhttps://orcid.org/0000-0002-1920-3364UNSPECIFIED
Ozawa, HiroshiTokyo Metropolitan UniversityUNSPECIFIEDUNSPECIFIED
Date:30 September 2019
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Hypersonic, boundary layer transition, HEG, hypersonic glider, HGV, HEXAFLY-INT, roughness induced transition
Event Title:FAR 2019 - International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering
Event Location:Monopoli, Italien
Event Type:international Conference
Event Start Date:30 September 2019
Event End Date:3 October 2019
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Wiederverwendbare Raumfahrtsysteme (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Institute for Aerodynamics and Flow Technology > Spacecraft, BS
Deposited By: Wagner, Alexander
Deposited On:07 Nov 2019 17:22
Last Modified:24 Apr 2024 20:33

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