Test Time Determination by End Wall Pressure Measurement in an Arc-Driven Shock Tube

AIAA Journal ◽  
1975 ◽  
Vol 13 (2) ◽  
pp. 255-256
Author(s):  
A. J. MULAC ◽  
J. L. MARK ◽  
J. A. GUZMAK
Keyword(s):  
Shock Tube ◽  
Pressure Measurement ◽  
Wall Pressure ◽  
Test Time ◽  
Time Determination ◽  
End Wall

Evaluation of blunt body velocity gradient at the shock tube end-wall

2020 ◽  
Vol 170 ◽  
pp. 570-576 ◽  
Author(s):  
Yosheph Yang ◽  
Ikhyun Kim ◽  
Gisu Park
Keyword(s):  
Shock Tube ◽  
Velocity Gradient ◽  
Blunt Body ◽  
Body Velocity ◽  
End Wall

scholarly journals Unsteady pressure measurement and numerical simulations in an end-wall region of a linear blade cascade

2021 ◽  
Vol 3 (8) ◽  
Author(s):  
Erik Flídr ◽  
Petr Straka ◽  
Milan Kladrubský ◽  
Tomáš Jelínek
Keyword(s):  
Numerical Simulations ◽  
Pressure Measurement ◽  
Power Spectra ◽  
Surface Flow ◽  
Wall Region ◽  
Suction Surface ◽  
Flow Angle ◽  
Unsteady Pressure ◽  
Flow Visualizations ◽  
End Wall

AbstractThis contribution describes experimental and numerical research of an unsteady behaviour of a flow in an end-wall region of a linear nozzle cascade. Effects of compressibility ($$M_\mathrm {2,is}$$ M 2 , is ) and inlet flow angle ($$\alpha _1$$ α 1 ) were investigated. Reynolds number ($$Re_\mathrm {2,is}$$ R e 2 , is $$=8.5\times 10^5$$ = 8.5 × 10 5 ) was held constant for all tested cases. Unsteady pressure measurement was performed at the blade mid-span in the identical position $${\mathfrak {s}}$$ s to obtain reference data. Surface flow visualizations were performed as well as the steady pressure measurement to support conclusions obtained from the unsteady measurements. Comparison of the surface Mach number distributions obtained from the experiments and from the numerical simulations are presented. Flow visualizations are then compared with calculated limiting streamlines on the blade suction surface. It was shown, that the flow structures in the end-wall region were not affected by the primary flow at the blade mid-span, even when the shock wave formed. This conclusion was made from the experimental, numerical, steady as well as unsteady points of view. Three significant frequencies in the power spectra suggested that there was a periodical interaction between the vortex structures in the end-wall region. Based on the data analyses, anisotropic turbulence was observed in the cascade.

scholarly journals Measurements of test time in the galcit 17-inch shock tube

AIAA Journal ◽  
1964 ◽  
Vol 2 (1) ◽  
pp. 186-187 ◽  
Author(s):  
ANATOL ROSHKO ◽  
JEROME A. SMITH
Keyword(s):  
Shock Tube ◽  
Test Time

The numerical simulation of shock bifurcation near the end wall of a shock tube

1995 ◽  
Vol 7 (10) ◽  
pp. 2475-2488 ◽  
Author(s):  
Y. S. Weber ◽  
E. S. Oran ◽  
J. P. Boris ◽  
J. D. Anderson
Keyword(s):  
Numerical Simulation ◽  
Shock Tube ◽  
End Wall

End-Wall Effects on Freely Propagating Flames in a Shock Tube

2022 ◽  
Author(s):  
Adam J. Susa ◽  
Lingzhi Zheng ◽  
Zach D. Nygaard ◽  
Ronald K. Hanson
Keyword(s):  
Shock Tube ◽  
Wall Effects ◽  
End Wall

scholarly journals Cavitation bubble wall pressure measurement by an electromagnetic surface wave enhanced pump-probe configuration

2019 ◽  
Vol 114 (13) ◽  
pp. 134101 ◽  
Author(s):  
Agostino Occhicone ◽  
Giorgia Sinibaldi ◽  
Norbert Danz ◽  
Carlo Massimo Casciola ◽  
Francesco Michelotti
Keyword(s):  
Surface Wave ◽  
Pressure Measurement ◽  
Cavitation Bubble ◽  
Wall Pressure ◽  
Bubble Wall ◽  
Pump Probe ◽  
Electromagnetic Surface Wave
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