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A joint study on the starting limits of a generic supersonic inlet

Schülein, Erich and Schenk, Manuel and Buchmann, Benedikt (2017) A joint study on the starting limits of a generic supersonic inlet. AIAA Aviation 2017, 05.-09. Juni 2017, Denver (CO), USA.

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Official URL: https://www.aiaa-aviation.org/Program/


The present work is a numerical and experimental study on the starting limits of a simplified generic supersonic inlet with the internal compression, which focuses primarily on the effect of the cowl-lip bluntness at different cowl-contour shapes and internal contraction rates. Apart from the baseline cowl-lip configuration (single ramp) two other geometries with the same flow inclination of 6 degree (double ramp and convex ramp) were investigated. The ranges of the incoming flow Mach number M (upstream of the cowl plate, M = 2.5 ... 3.0) and of the internal contraction ratio (K = 2.0 ... 2.5) were determined to ensure the existence of a complete set of flow stages between the started and unstarted modes. The results confirm a very strong impact of the cowl-lip bluntness on the critical Mach number, which could be quantified for the model configurations studied.

Item URL in elib:https://elib.dlr.de/110937/
Document Type:Conference or Workshop Item (Speech)
Title:A joint study on the starting limits of a generic supersonic inlet
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Schülein, ErichErich.Schuelein (at) dlr.dehttps://orcid.org/0000-0002-1125-8504
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Lufteinlauf, Überschall, Experiment, Simulation
Event Title:AIAA Aviation 2017
Event Location:Denver (CO), USA
Event Type:international Conference
Event Dates:05.-09. Juni 2017
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies (old)
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Bachmann, Barbara
Deposited On:13 Dec 2017 14:42
Last Modified:13 Dec 2017 14:42

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