Abstract
This paper presents an experimental technique to estimate the appropriate thermal product values of rugged and fast response temperature probes (TPs) for hypersonic aerodynamic experiments. Two types of scratches were used, mainly abrasive papers with different grit sizes and scalpel blades with different thicknesses, to form the probe junction. The effect of the scratch technique on the probe's thermal product is investigated. The probes are tested and calibrated in the test section and in the end wall of shock tube facility. It is observed that the thermal product of a particular TP depends on the Mach number, junction scratch technique, and junction location, as well as on the enthalpy conditions. It is noted that, depending on the scratch technique, some of the TPs do not require individual calibration; however, calibration for others is likely to be needed.
| Original language | English |
|---|---|
| Pages (from-to) | 849-859 |
| Number of pages | 11 |
| Journal | Journal of Engineering Physics and Thermophysics |
| Volume | 84 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - 01 Jul 2011 |
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All Science Journal Classification (ASJC) codes
- Condensed Matter Physics
- Engineering(all)
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Thermal product estimation method for aerodynamics experiments. / Mohammed, H. A.; Salleh, Hanim; Yusoff, Mohd Zamri.
In: Journal of Engineering Physics and Thermophysics, Vol. 84, No. 4, 01.07.2011, p. 849-859.Research output: Contribution to journal › Article
TY - JOUR
T1 - Thermal product estimation method for aerodynamics experiments
AU - Mohammed, H. A.
AU - Salleh, Hanim
AU - Yusoff, Mohd Zamri
PY - 2011/7/1
Y1 - 2011/7/1
N2 - This paper presents an experimental technique to estimate the appropriate thermal product values of rugged and fast response temperature probes (TPs) for hypersonic aerodynamic experiments. Two types of scratches were used, mainly abrasive papers with different grit sizes and scalpel blades with different thicknesses, to form the probe junction. The effect of the scratch technique on the probe's thermal product is investigated. The probes are tested and calibrated in the test section and in the end wall of shock tube facility. It is observed that the thermal product of a particular TP depends on the Mach number, junction scratch technique, and junction location, as well as on the enthalpy conditions. It is noted that, depending on the scratch technique, some of the TPs do not require individual calibration; however, calibration for others is likely to be needed.
AB - This paper presents an experimental technique to estimate the appropriate thermal product values of rugged and fast response temperature probes (TPs) for hypersonic aerodynamic experiments. Two types of scratches were used, mainly abrasive papers with different grit sizes and scalpel blades with different thicknesses, to form the probe junction. The effect of the scratch technique on the probe's thermal product is investigated. The probes are tested and calibrated in the test section and in the end wall of shock tube facility. It is observed that the thermal product of a particular TP depends on the Mach number, junction scratch technique, and junction location, as well as on the enthalpy conditions. It is noted that, depending on the scratch technique, some of the TPs do not require individual calibration; however, calibration for others is likely to be needed.
UR - http://www.scopus.com/inward/record.url?scp=80055006997&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=80055006997&partnerID=8YFLogxK
U2 - 10.1007/s10891-011-0542-4
DO - 10.1007/s10891-011-0542-4
M3 - Article
AN - SCOPUS:80055006997
VL - 84
SP - 849
EP - 859
JO - Journal of Engineering Physics and Thermophysics
JF - Journal of Engineering Physics and Thermophysics
SN - 1062-0125
IS - 4
ER -