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Free-flight measurement technique in the free-piston high-enthalpy shock tunnel

Tanno, H. and Komuro, T. and Sato, K. and Fujita, K. and Laurence, Stuart (2014) Free-flight measurement technique in the free-piston high-enthalpy shock tunnel. Review of Scientific Instruments, 85 (4), pp. 1-8. American Institute of Physics (AIP). doi: 10.1063/1.4870920. ISSN 0034-6748.

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Official URL: http://dx.doi.org/10.1063/1.4870920


A novel multi-component force-measurement technique has been developed and implemented at the impulse facility JAXA-HIEST, in which the test model is completely unrestrained during the test and thus experiences free-flight conditions for a period on the order of milliseconds. Advantages over conventional free-flight techniques include the complete absence of aerodynamic interference from a model support system and less variation in model position and attitude during the test itself. A miniature on-board data recorder, which was a key technology for this technique, was also developed in order to acquire and store the measured data. The technique was demonstrated in a HIEST windtunnel test campaign in which three-component aerodynamic force measurement was performed on a blunted cone of length 316 mm, total mass 19.75 kg, and moment of inertia 0.152 kgm2. During the test campaign, axial force, normal forces, and pitching moment coefficients were obtained at angles of attack from 14° to 32° under two conditions: H0 = 4 MJ/kg, P0 = 14 MPa; and H0 = 16 MJ/kg, P0 = 16 MPa. For the first, low-enthalpy condition, the test flow was considered a perfect gas; measurements were thus directly compared with those obtained in a conventional blow-down wind tunnel (JAXA-HWT2) to evaluate the accuracy of the technique. The second test condition was a high-enthalpy condition in which 85% of the oxygen molecules were expected to be dissociated; high-temperature real-gas effects were therefore evaluated by comparison with results obtained in perfect-gas conditions. The precision of the present measurements was evaluated through an uncertainty analysis, which showed the aerodynamic coefficients in the HIEST low enthalpy test agreeing well with those of JAXA-HWT2. The pitching-moment coefficient, however, showed significant differences between low- and high-enthalpy tests. These differences are thought to result from hightemperature real-gas effects.

Item URL in elib:https://elib.dlr.de/95319/
Document Type:Article
Additional Information:http://scitation.aip.org/content/aip/journal/rsi/85/4?ver=pdfcov; Published online: 15 April 2014, Paper: 045112
Title:Free-flight measurement technique in the free-piston high-enthalpy shock tunnel
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Tanno, H.Japan Aerospace Exploration Agency, Kakuda Space Center, Kakuda Miyagi 981-1525, JapanUNSPECIFIED
Komuro, T.Japan Aerospace Exploration Agency, Kakuda Space Center, Kakuda Miyagi 981-1525, JapanUNSPECIFIED
Sato, K.Japan Aerospace Exploration Agency, Kakuda Space Center, Kakuda Miyagi 981-1525, JapanUNSPECIFIED
Fujita, K.Japan Aerospace Exploration Agency, Chofu Aerospace Center, Chofu Tokyo 182-8522, JapanUNSPECIFIED
Laurence, Stuartstuart.laurence (at) dlr.deUNSPECIFIED
Journal or Publication Title:Review of Scientific Instruments
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.1063/1.4870920
Page Range:pp. 1-8
Publisher:American Institute of Physics (AIP)
Keywords:free-flight technique, high-enthalpy facility, force balance
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:25 Feb 2015 15:24
Last Modified:06 Sep 2019 15:29

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