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Experimental Investigation of Boundary Layer Transition on a Supersonic Swept Wing

Schülein, Erich (2005) Experimental Investigation of Boundary Layer Transition on a Supersonic Swept Wing. DLR-Interner Bericht. DLR-IB 224 - 2005 A 15, 25 S. DLR Göttingen.

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Abstract

The laminar-turbulent transition on a swept-wing leading-edge model at Mach 3 is investigated. The experiments are obtained in the Ludwieg Tube Facility at DLR Göttingen. The data contain surface pressure distributions, the location of the transition region, the structure of the limiting streamlines as well as some quantitative skin friction distributions at the upper side of the swept-wing model for the range of the unit Reynolds number and angles of attack at two different leading-edge shapes.

Item URL in elib:https://elib.dlr.de/21726/
Document Type:Monograph (DLR-Interner Bericht)
Title:Experimental Investigation of Boundary Layer Transition on a Supersonic Swept Wing
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Schülein, ErichUNSPECIFIEDUNSPECIFIED
Date:September 2005
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Number of Pages:25
Publisher:DLR Göttingen
Status:Published
Keywords:Transition, Swept Wing, Experiment, Skin Friction
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Schülein, Dr.rer.nat. Erich
Deposited On:26 Jan 2006
Last Modified:27 Apr 2009 04:56

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