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Fast‑response temperature‑sensitive‑paint measurements on a hypersonic transition cone

Ozawa, Hiroshi and Laurence, Stuart Jon and Martinez Schramm, Jan and Wagner, Alexander and Hannemann, Klaus (2015) Fast‑response temperature‑sensitive‑paint measurements on a hypersonic transition cone. Experiments in Fluids, 56 (1), pp. 1-13. Springer Nature. doi: 10.1007/s00348-014-1853-y. ISSN 0723-4864.

Full text not available from this repository.

Official URL: http://link.springer.com/article/10.1007/s00348-014-1853-y/fulltext.html

Abstract

Experiments are performed using a fastresponse temperature-sensitive-paint (TSP) technique to measure the heat-flux distribution on a slender cone in a hypersonic shock tunnel under both laminar and transitional conditions. The millisecond-order test duration together with the self-luminosity of shock layers place stringent conditions on the choice of TSP luminophore and the TSP-layer thickness that can be employed. The luminosity and dimming from particulates in the free-stream cause additional problems in interpreting the obtained intensity profiles. Nevertheless, favorable agreement with thermocouple-based measurements show that it is possible to derive quantitatively accurate heat-flux distributions with the TSP technique for temperature rises of up to approximately 40 K above room temperature. The technique accuracy is adversely affected at higher temperatures, which is thought to result from non-constant thermal properties of the insulating base layer. At high unit Reynolds number conditions, time-resolved heat-flux distributions show large-scale unsteadiness in the boundary-layer transition location and reveal transient streamwise streaks developing in the transitional region.

Item URL in elib:https://elib.dlr.de/93897/
Document Type:Article
Additional Information:Published online: 07. Dec. 2014, Article: 1853
Title:Fast‑response temperature‑sensitive‑paint measurements on a hypersonic transition cone
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Ozawa, HiroshiUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Laurence, Stuart JonDept. of Aerospace Engineering, University of MarylandUNSPECIFIEDUNSPECIFIED
Martinez Schramm, JanUNSPECIFIEDhttps://orcid.org/0000-0002-8891-6253UNSPECIFIED
Wagner, AlexanderUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Hannemann, KlausUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Date:2015
Journal or Publication Title:Experiments in Fluids
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:56
DOI:10.1007/s00348-014-1853-y
Page Range:pp. 1-13
Publisher:Springer Nature
ISSN:0723-4864
Status:Published
Keywords:temperature-sensitive-paint (TSP), hypersonic shock tunnel, boundary-layer transition, streamwise streaks
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 - Raumfahrzeugsysteme - Anlagen u. Messtechnik (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Micknaus, Ilka
Deposited On:19 Dec 2014 16:17
Last Modified:12 May 2023 13:04

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