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Sharp Leading Edge at Hypersonic Flight: Modeling and Flight Measurement

Böhrk, Hannah and Thiele, Thomas and Dittert, Christian and Weihs, Hendrik and Gülhan, Ali (2014) Sharp Leading Edge at Hypersonic Flight: Modeling and Flight Measurement. Journal of Spacecraft and Rockets, 51 (5), pp. 1753-1760. American Institute of Aeronautics and Astronautics (AIAA). DOI: http://arc.aiaa.org/doi/abs/10.2514/1.A32892 ISSN 0022-4650

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The octahedral sharp leading edge of the sharp edge flight experiment SHEFEX II is made from carbon fiber reinforced ceramic with a tip radius of <1 mm. It is instrumented by thermocouples and pressure ports and the measurement values are compared with a theoretical model. A duplicate was ground tested in the arc-heated wind tunnel L3K. During ground testing, the thermocouples measured up to 1219°C, with the very tip of the leading edge reaching 1635°C, and the leading edge was in good order after testing. Transient thermal response of the material to the aerothermodynamic load was simulated by the heat balance method Heat Exchange Analysis for Transpiration Systems and compared with the measurement data. The data correspond well to both thermocouple data and data from an external infrared camera. During the ballistic return flight between Mach 10.2 and 9.3, the maximum temperature transmitted to the ground station was measured at 30km altitude with 867°C just before the vehicle dove behind the horizon. The heat balance predicts the measurement with an accuracy on the order of 10%.

Item URL in elib:https://elib.dlr.de/91996/
Document Type:Article
Title:Sharp Leading Edge at Hypersonic Flight: Modeling and Flight Measurement
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Thiele, ThomasInstitut für Aerodynamik und StrömungstechnikUNSPECIFIED
Gülhan, AliInstitut für Aerodynamik und StrömungstechnikUNSPECIFIED
Date:9 October 2014
Journal or Publication Title:Journal of Spacecraft and Rockets
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :http://arc.aiaa.org/doi/abs/10.2514/1.A32892
Page Range:pp. 1753-1760
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:TPS active cooling transpiration SHEFEX efficiency
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:23 Dec 2014 17:32
Last Modified:08 Mar 2018 18:45

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