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Transpiration-Cooled Hypersonic Flight Experiment: Setup, Flight Measurement, and Reconstruction

Böhrk, Hannah (2015) Transpiration-Cooled Hypersonic Flight Experiment: Setup, Flight Measurement, and Reconstruction. Journal of Spacecraft and Rockets, 52 (3), pp. 674-683. American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.A33144 ISSN 0022-4650

Full text not available from this repository.

Official URL: http://arc.aiaa.org/doi/pdf/10.2514/1.A33144

Abstract

The present paper presents the in-flight measurement of the transpiration cooling experiment Aktive Kühlung durch Transpiration im Versuch (often referred to as AKTiV) flown on the suborbital reentry configuration Sharp Edge Flight Experiment II (often referred to as SHEFEX II). Thermal response of the structure is measured just up and downstream of a cooled sample with a noncooled reference setup on the opposite side of the vehicle. The measurement shows that the heat flux is reduced upon coolant exhaust. The maximum temperature reduction with 87 K is observed on the porous sample, while downstream the sample, the temperature is reduced by 75 K by film cooling. This corresponds to cooling efficiencies of 58 and 42% on the sample and downstream, respectively. The evaluation is supported by the semi-analytical tool HEATS, based on a transient heat balance at the surface. Comparison of the results with HEATS shows that the heat flux predicted with HEATS is in good concurrence with the measured temperatures on the cooled sample, as well as upstream and downstream with a maximum deviation by 14%. The analysis suggests that the flow condition around the sharp-edged, faceted vehicle remained laminar longer than expected.

Item URL in elib:https://elib.dlr.de/98674/
Document Type:Article
Title:Transpiration-Cooled Hypersonic Flight Experiment: Setup, Flight Measurement, and Reconstruction
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Böhrk, HannahHannah.Boehrk (at) dlr.deUNSPECIFIED
Date:2015
Journal or Publication Title:Journal of Spacecraft and Rockets
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:52
DOI :10.2514/1.A33144
Page Range:pp. 674-683
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0022-4650
Status:Published
Keywords:transpiration, effuion, cooling, SHEFEX II, heat shield
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Shefex III
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space System Integration
Deposited By: Böhrk, Hannah
Deposited On:13 Jan 2016 11:45
Last Modified:08 Mar 2018 18:45

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