Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows

Hartmut Borchert; Stefan Brieschenk; Berthold Sauerwein

doi:doi:10.11648/j.ep.20190302.11

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Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows

Hartmut Borchert, Stefan Brieschenk, Berthold Sauerwein

Published in Engineering Physics (Volume 3, Issue 2)

Received: 25 September 2019 Accepted: 11 October 2019 Published: 2 December 2019

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Abstract

This paper demonstrates time-resolved stagnation temperature measurements in a shock tunnel at a frequency of 25 kHz using emission spectroscopy in air and nitrogen test conditions. The two most important parameters for determining the flow conditions generated in a shock tunnel experiment are the stagnation pressure and temperature of the flow just upstream of the supersonic nozzle. While the pressure can be measured using a wall-mounted transducer with relative ease, the measurement of the temperature requires a optical technique such as time resolved emission spectroscopy. Knowledge of the transient stagnation temperature behavior is critical to all subsequent expansion tube flow processes. The driver gas emission spectrum data at the post-shock condition shows continuum and atomic line radiation. The continuum radiation can be described by a black body radiator with the individual spectra showing sufficient continuum information for accurately fitting Planck functions. Atomic line radiation was excluded by skipping those data from the measured spectra. The fitting routine shows clear differences in determined temperatures including and neglecting atomic line radiation. These measurements allow for the exact determination of the shock tunnel flow conditions in combination with pressure transducer data. The flow condition used in the experiment corresponds to a nominal Mach-10 condition at an altitude of 65 km, however, the technique is not limited to this condition and can be used for a large range of flow conditions.

Published in	Engineering Physics (Volume 3, Issue 2)
DOI	10.11648/j.ep.20190302.11
Page(s)	6-11
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2019. Published by Science Publishing Group

Keywords

Shock-Tunnel, Stagnation Temperature, Emission Spectroscopy, Continuum Emission

References

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[2]	Shock tunnels at ISL, ISL-U-PU 6106/2016.
[3]	Zeitaufgelößte Strahldichtemessungen an stoßwellen-induzierten Blitzen in Argon, Luft und Xenon, ISL R 120 / 94.
[4]	M. R. E. Lamont, Y. Okawachi, and A. L. Gaeta, “Study about lasers and optics,” Opt. Lett. 38, 3478 (2013).
[5]	Fujii, T., Fukuchi, T., Laser Remote Sensing, CRC Press 2005.
[6]	Thorne, A., Litzen, U., Spectrophysics: Principles and Applications, Germany, Springer, Berlin, Heidelberg, 1999.
[7]	D. Meiners, Spektroskopische Methoden zur Messung der Temperatur in Plasmen mit Selbstabsorption, Bundesministerium für Bildung und Wissenschaft, Forschungsbericht K 72-22.
[8]	Eichhorn, A., Werner, U., Zeitaufgelößte Temperaturmessung in Strömungen mit Rotationssymmetrie.
[9]	S. W. Bowen, Spectroscopic and optical studies of a high pressure underexpanded jet, AIAA Plasmadynamics Conference, March 2-4, 1966.
[10]	Buttsworth, D R., Jacobs, P. A., Total temperature measurement in a shock tunnel facility, 13th Australasian Fluid Mechanics Conference Monash University, Melbourne, Australia, 1998.
[11]	O’Byrne, S., Altenhofer, P., Time resolved temperature measurements in a shock tube facility, 16th Australasian Fluid Mechanics Conference School of Engineering, The University of Queensland, 2007, pp. 1171-1176.
[12]	East, R., Perry, J., A short time response stagnation temperature probe, National Advisory Committee for Aeronautics, 1966.
[13]	Widodo, A., Buttsworth, D., Stagnation temperature measurements in the USQ hypersonic wind tunnel, 17th Australasian Fluid Mechanics Conference Vol. 248, University of Auckland, 2010, pp. 840-844.
[14]	Devia, D., M. Rodriguez-Restrepo, L. V., Methods employed in optical emission spectroscopy analysis, a review, Ingenieria y Ciencia-Universidad EAFIT, Vol. 11, No. 21, 2014, pp. 239-267.
[15]	NIST, Atomic Spectra Database, Lines Data, MD 2015.
[16]	Hirata, R., Horagucci, T., Atomic Spectral Line List, ftp://cdsarc.u-strasbg.fr/VI/69.

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APA Style

Hartmut Borchert, Stefan Brieschenk, Berthold Sauerwein. (2019). Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Engineering Physics, 3(2), 6-11. https://doi.org/10.11648/j.ep.20190302.11

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ACS Style

Hartmut Borchert; Stefan Brieschenk; Berthold Sauerwein. Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Eng. Phys. 2019, 3(2), 6-11. doi: 10.11648/j.ep.20190302.11

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AMA Style

Hartmut Borchert, Stefan Brieschenk, Berthold Sauerwein. Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Eng Phys. 2019;3(2):6-11. doi: 10.11648/j.ep.20190302.11

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@article{10.11648/j.ep.20190302.11,
  author = {Hartmut Borchert and Stefan Brieschenk and Berthold Sauerwein},
  title = {Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows},
  journal = {Engineering Physics},
  volume = {3},
  number = {2},
  pages = {6-11},
  doi = {10.11648/j.ep.20190302.11},
  url = {https://doi.org/10.11648/j.ep.20190302.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ep.20190302.11},
  abstract = {This paper demonstrates time-resolved stagnation temperature measurements in a shock tunnel at a frequency of 25 kHz using emission spectroscopy in air and nitrogen test conditions. The two most important parameters for determining the flow conditions generated in a shock tunnel experiment are the stagnation pressure and temperature of the flow just upstream of the supersonic nozzle. While the pressure can be measured using a wall-mounted transducer with relative ease, the measurement of the temperature requires a optical technique such as time resolved emission spectroscopy. Knowledge of the transient stagnation temperature behavior is critical to all subsequent expansion tube flow processes. The driver gas emission spectrum data at the post-shock condition shows continuum and atomic line radiation. The continuum radiation can be described by a black body radiator with the individual spectra showing sufficient continuum information for accurately fitting Planck functions. Atomic line radiation was excluded by skipping those data from the measured spectra. The fitting routine shows clear differences in determined temperatures including and neglecting atomic line radiation. These measurements allow for the exact determination of the shock tunnel flow conditions in combination with pressure transducer data. The flow condition used in the experiment corresponds to a nominal Mach-10 condition at an altitude of 65 km, however, the technique is not limited to this condition and can be used for a large range of flow conditions.},
 year = {2019}
}

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TY  - JOUR
T1  - Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows
AU  - Hartmut Borchert
AU  - Stefan Brieschenk
AU  - Berthold Sauerwein
Y1  - 2019/12/02
PY  - 2019
N1  - https://doi.org/10.11648/j.ep.20190302.11
DO  - 10.11648/j.ep.20190302.11
T2  - Engineering Physics
JF  - Engineering Physics
JO  - Engineering Physics
SP  - 6
EP  - 11
PB  - Science Publishing Group
SN  - 2640-1029
UR  - https://doi.org/10.11648/j.ep.20190302.11
AB  - This paper demonstrates time-resolved stagnation temperature measurements in a shock tunnel at a frequency of 25 kHz using emission spectroscopy in air and nitrogen test conditions. The two most important parameters for determining the flow conditions generated in a shock tunnel experiment are the stagnation pressure and temperature of the flow just upstream of the supersonic nozzle. While the pressure can be measured using a wall-mounted transducer with relative ease, the measurement of the temperature requires a optical technique such as time resolved emission spectroscopy. Knowledge of the transient stagnation temperature behavior is critical to all subsequent expansion tube flow processes. The driver gas emission spectrum data at the post-shock condition shows continuum and atomic line radiation. The continuum radiation can be described by a black body radiator with the individual spectra showing sufficient continuum information for accurately fitting Planck functions. Atomic line radiation was excluded by skipping those data from the measured spectra. The fitting routine shows clear differences in determined temperatures including and neglecting atomic line radiation. These measurements allow for the exact determination of the shock tunnel flow conditions in combination with pressure transducer data. The flow condition used in the experiment corresponds to a nominal Mach-10 condition at an altitude of 65 km, however, the technique is not limited to this condition and can be used for a large range of flow conditions.
VL  - 3
IS  - 2
ER  -

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Author Information

Hartmut Borchert

French-German Research Institute of Saint-Louis, Saint-Louis Cedex, France
Stefan Brieschenk

French-German Research Institute of Saint-Louis, Saint-Louis Cedex, France
Berthold Sauerwein

French-German Research Institute of Saint-Louis, Saint-Louis Cedex, France

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Plain Text BibTeX RIS

APA Style

Hartmut Borchert, Stefan Brieschenk, Berthold Sauerwein. (2019). Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Engineering Physics, 3(2), 6-11. https://doi.org/10.11648/j.ep.20190302.11

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ACS Style

Hartmut Borchert; Stefan Brieschenk; Berthold Sauerwein. Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Eng. Phys. 2019, 3(2), 6-11. doi: 10.11648/j.ep.20190302.11

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AMA Style

Hartmut Borchert, Stefan Brieschenk, Berthold Sauerwein. Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows. Eng Phys. 2019;3(2):6-11. doi: 10.11648/j.ep.20190302.11

Copy | Download

@article{10.11648/j.ep.20190302.11,
  author = {Hartmut Borchert and Stefan Brieschenk and Berthold Sauerwein},
  title = {Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows},
  journal = {Engineering Physics},
  volume = {3},
  number = {2},
  pages = {6-11},
  doi = {10.11648/j.ep.20190302.11},
  url = {https://doi.org/10.11648/j.ep.20190302.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ep.20190302.11},
  abstract = {This paper demonstrates time-resolved stagnation temperature measurements in a shock tunnel at a frequency of 25 kHz using emission spectroscopy in air and nitrogen test conditions. The two most important parameters for determining the flow conditions generated in a shock tunnel experiment are the stagnation pressure and temperature of the flow just upstream of the supersonic nozzle. While the pressure can be measured using a wall-mounted transducer with relative ease, the measurement of the temperature requires a optical technique such as time resolved emission spectroscopy. Knowledge of the transient stagnation temperature behavior is critical to all subsequent expansion tube flow processes. The driver gas emission spectrum data at the post-shock condition shows continuum and atomic line radiation. The continuum radiation can be described by a black body radiator with the individual spectra showing sufficient continuum information for accurately fitting Planck functions. Atomic line radiation was excluded by skipping those data from the measured spectra. The fitting routine shows clear differences in determined temperatures including and neglecting atomic line radiation. These measurements allow for the exact determination of the shock tunnel flow conditions in combination with pressure transducer data. The flow condition used in the experiment corresponds to a nominal Mach-10 condition at an altitude of 65 km, however, the technique is not limited to this condition and can be used for a large range of flow conditions.},
 year = {2019}
}

Copy | Download

TY  - JOUR
T1  - Time-Resolved On-Axis Spectroscopic Stagnation Temperature Measurements in Shock Tunnel Flows
AU  - Hartmut Borchert
AU  - Stefan Brieschenk
AU  - Berthold Sauerwein
Y1  - 2019/12/02
PY  - 2019
N1  - https://doi.org/10.11648/j.ep.20190302.11
DO  - 10.11648/j.ep.20190302.11
T2  - Engineering Physics
JF  - Engineering Physics
JO  - Engineering Physics
SP  - 6
EP  - 11
PB  - Science Publishing Group
SN  - 2640-1029
UR  - https://doi.org/10.11648/j.ep.20190302.11
AB  - This paper demonstrates time-resolved stagnation temperature measurements in a shock tunnel at a frequency of 25 kHz using emission spectroscopy in air and nitrogen test conditions. The two most important parameters for determining the flow conditions generated in a shock tunnel experiment are the stagnation pressure and temperature of the flow just upstream of the supersonic nozzle. While the pressure can be measured using a wall-mounted transducer with relative ease, the measurement of the temperature requires a optical technique such as time resolved emission spectroscopy. Knowledge of the transient stagnation temperature behavior is critical to all subsequent expansion tube flow processes. The driver gas emission spectrum data at the post-shock condition shows continuum and atomic line radiation. The continuum radiation can be described by a black body radiator with the individual spectra showing sufficient continuum information for accurately fitting Planck functions. Atomic line radiation was excluded by skipping those data from the measured spectra. The fitting routine shows clear differences in determined temperatures including and neglecting atomic line radiation. These measurements allow for the exact determination of the shock tunnel flow conditions in combination with pressure transducer data. The flow condition used in the experiment corresponds to a nominal Mach-10 condition at an altitude of 65 km, however, the technique is not limited to this condition and can be used for a large range of flow conditions.
VL  - 3
IS  - 2
ER  -

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