Boundary Layer Profile Behind Gaseous Detonation as it Affects Reflected Shock Wave Bifurcation
The present study explores the flow field created by reflecting detonations using heat transfer and pressure measurements near the location of detonation reflection. Schlieren imaging techniques are used to examine the possibility of shock wave-boundary layer interaction. These measurements are compared to laminar boundary layer theory and a one- dimensional model of detonation reflection. Experiments were carried out in a 7.6 m long detonation tube with a rectangular test section using mixtures of stoichiometric hydrogen- oxygen with argon dilution of 0, 50, 67, and 83% at an initial pressure of 10, 25, and 40 kPa. Optical observations show that minimal interaction of the reflected shock wave results when propagating into the boundary layer created by the incident wave. The heat transfer rate is qualitatively consistent with the time dependent laminar boundary layer predictions, however the magnitude is consistently larger and substantial (factor of three) peak-to-peak fluctuations are observed. The pressure measurements show good agreement between predicted ideal incident and reflected wave speeds. The pressure amplitudes are under-predicted for no argon dilution cases particularly at 40 kPa, but in reasonable agreement for lower pressures and higher dilutions.
Additional Information© 2012 American Institute of Aeronautics and Astronautics. This research is sponsored by the DHS through the University of Rhode Island, Center of Excellence for Explosives Detection. The authors would also like to thank Bahram Valiferdowsi for his help in designing the splitter plate as well as the Caltech SURF program for sponsoring Jeff Odell.
Published - DamazoAIAA2012.pdf