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Determination of heat transfer into a wedge model in a hypersonic flow using temperature-sensitive paint

Risius, Steffen and Beck, Walter H. and Klein, Christian and Henne, Ulrich and Wagner, Alexander (2017) Determination of heat transfer into a wedge model in a hypersonic flow using temperature-sensitive paint. Experiments in Fluids, 58 (9), pp. 1-13. Springer. DOI: 10.1007/s00348-017-2393-z ISSN 0723-4864

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Official URL: https://doi.org/10.1007/s00348-017-2393-z

Abstract

Heat loads on spacecraft traveling at hypersonic speed are of major interest for their designers. Several tests using temperature-sensitive paints (TSP) have been carried out in long duration shock tunnels to determine these heat loads; generally paint layers were thin, so that certain assumptions could be invoked to enable a good estimate of the thermal parameter rho.c.k (a material property) to be obtained - the value of this parameter is needed to determine heat loads from the TSP. Very few measurements have been carried out in impulse facilities (viz. shock tunnels such as the High Enthalpy Shock Tunnel Göttingen (HEG)), where test times are much shorter. Presented here are TSP temperature measurements and subsequently derived heat loads on a ramp model placed in a hypersonic flow in HEG (specific enthalpy h0 = 3.3 MJ/kg, Mach number M = 7.4, temperature T_inf = 277 K, density rho_inf = 11 g/m^3). A number of fluorescence intensity images were acquired, from which, with the help of calibration data, temperature field data on the model surface were determined. From these the heat load into the surface was calculated, using an assumption of a 1D, semi-infinite heat transfer model. rho.c.k for the paint was determined using an insitu calibration with a Medtherm coaxial thermocouple mounted on the model; Medtherm rho.c.k is known. Finally presented are sources of various measurement uncertainties, arising from: (1) estimation of rho.c.k; (2) intensity measurement in the chosen interrogation area; (3) paint time response.

Item URL in elib:https://elib.dlr.de/116926/
Document Type:Article
Additional Information:Published online: 03 August 2017; Article 117; ISSN:1432-1114 (Online) Cite this article as: Risius, Steffen und Beck, Walter H. und Klein, Christian und Henne, Ulrich und Wagner, Alexander (2017) Determination of heat transfer into a wedge model in a hypersonic flow using temperature-sensitive paint. Experiments in Fluids 58:117. Springer-Verlag GmbH Germany 2017. DOI: 10.1007/s00348-017-2393-z
Title:Determination of heat transfer into a wedge model in a hypersonic flow using temperature-sensitive paint
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Risius, Steffensteffen.risius (at) dlr.dehttps://orcid.org/0000-0002-5530-9609
Beck, Walter H.walter.beck (at) dlr.deUNSPECIFIED
Klein, ChristianChristian.Klein (at) dlr.deUNSPECIFIED
Henne, Ulrichulrich.henne (at) dlr.deUNSPECIFIED
Wagner, AlexanderAlexander.Wagner (at) dlr.deUNSPECIFIED
Date:3 August 2017
Journal or Publication Title:Experiments in Fluids
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:58
DOI :10.1007/s00348-017-2393-z
Page Range:pp. 1-13
Publisher:Springer
ISSN:0723-4864
Status:Published
Keywords:Temperature Sensitive Paint (TSP), heat transfer, High Enthalpy Shock Tunnel (HEG), hypersonic flow
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 - Simulation and Validation
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Experimental Methods, GO
Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Bachmann, Barbara
Deposited On:13 Dec 2017 14:36
Last Modified:06 Sep 2019 15:25

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