TY - GEN
T1 - Krypton tagging velocimetry in the Stevens shock tube
AU - Mustafa, M. A.
AU - Parziale, N. J.
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - Krypton Tagging Velocimetry (KTV) is implemented in the flow immediately following the incident shock wave in the Stevens Shock Tube. This is motivated by the long-term goal of using KTV to measure velocity in large-scale impulse facilities. Two example cases are presented in 99% N2/1% Kr at incident shock Mach numbers of 2.86 and 2.94. The velocities as measured by KTV are, in general, higher than those calculated from the shock-speed measurements. The discrepancy is most likely due to the misalignment of splitter plate installed in the shock tube (an expansion fan likely accelerated the flow). A new excitation scheme for KTV is used that results in a higher SNR as compared to previous work. A justification of the alternate scheme is presented via a three energy level model. An overview of the shock tube is given, and a model predicting the non-equilibrium thermodynamic state of the gas immediately following the incident shock is presented.
AB - Krypton Tagging Velocimetry (KTV) is implemented in the flow immediately following the incident shock wave in the Stevens Shock Tube. This is motivated by the long-term goal of using KTV to measure velocity in large-scale impulse facilities. Two example cases are presented in 99% N2/1% Kr at incident shock Mach numbers of 2.86 and 2.94. The velocities as measured by KTV are, in general, higher than those calculated from the shock-speed measurements. The discrepancy is most likely due to the misalignment of splitter plate installed in the shock tube (an expansion fan likely accelerated the flow). A new excitation scheme for KTV is used that results in a higher SNR as compared to previous work. A justification of the alternate scheme is presented via a three energy level model. An overview of the shock tube is given, and a model predicting the non-equilibrium thermodynamic state of the gas immediately following the incident shock is presented.
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U2 - 10.2514/6.2017-3897
DO - 10.2514/6.2017-3897
M3 - Conference contribution
AN - SCOPUS:85088203597
SN - 9781624105029
T3 - 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 2017
BT - 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 2017
T2 - 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, 2017
Y2 - 5 June 2017 through 9 June 2017
ER -