elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical and experimental investigation of laminar-turbulent boundary layer transition on a blunt generic re-entry capsule

Theiß, Alexander and Hein, Stefan and Heitmann, Dirk and Ali, Syed Raza Christopher and Radespiel, Rolf (2014) Numerical and experimental investigation of laminar-turbulent boundary layer transition on a blunt generic re-entry capsule. American Institute of Aeronautics and Astronautics. AIAA Aviation and Aeronautics Forum and Exposition 2014, 16. - 20. June 2014, Atlanta, Georgia, USA.

Full text not available from this repository.

Official URL: http://arc.aiaa.org | DOI: 10.2514/6.2014-2353

Abstract

Numerical and experimental results on laminar-turbulent transition in the boundary layer of a blunt Apollo-like capsule at 0° and 24° angle of attack are presented. Local stability analyses have been performed and a measurement campaign in the Hypersonic Ludwieg tube Braunschweig at a Mach number of 5.9 was carried out. Infrared thermography showed laminar and transitional surface heating in the unit Reynolds number range of Re_infinity = 6x10^6 /m to Re_infinity = 20x10^6 /m at a surface mean roughness of Ra = 10 micrometer, whereas for a mean roughness of Ra = 0.5 My micrometer no indications for a transitional boundary layer was noted. PCB and Kulite sensors used to measure pressure fluctuations inside the boundary layer do not show any peaks in the frequency spectra which might be related to boundary layer disturbances. The only relevant peak in the spectra does not change with unit Reynolds number and is currently attributed to a bow shock oscillation. Consistent with the experimental findings, the modal instability analysis does not provide any modal boundary layer disturbance growth at windtunnel conditions. Therefore, a scaling ansatz for the laminar boundary layer is introduced and evaluated in order to estimate the unit Reynolds numbers required for the onset of modal disturbance growth on Apollo-like capsules. Results for both first-mode and cross-flow instability are presented.

Item URL in elib:https://elib.dlr.de/85443/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA 2014-2353, 44th AIAA Fluid Dynamics Conference, DOI: 10.2514/6.2014-2353
Title:Numerical and experimental investigation of laminar-turbulent boundary layer transition on a blunt generic re-entry capsule
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Theiß, Alexanderalexander.theiss (at) dlr.deUNSPECIFIED
Hein, Stefanstefan.hein (at) dlr.deUNSPECIFIED
Heitmann, DirkTechnische Universität BraunschweigUNSPECIFIED
Ali, Syed Raza ChristopherTechnische Universität BraunschweigUNSPECIFIED
Radespiel, RolfTU BraunschweigUNSPECIFIED
Date:2014
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 1-18
Publisher:American Institute of Aeronautics and Astronautics
Series Name:Conference Proceedings Online
Status:Published
Keywords:re-entry capsule, blunt body, transition, roughness elemen
Event Title:AIAA Aviation and Aeronautics Forum and Exposition 2014
Event Location:Atlanta, Georgia, USA
Event Type:international Conference
Event Dates:16. - 20. June 2014
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 - Flight Physics
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Micknaus, Ilka
Deposited On:17 Jul 2014 10:08
Last Modified:07 Nov 2014 13:45

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.