Using a shock tube to generate shock waves, the wave patterns through several bifurcated junctions were studied. The effect of roughness was simulated by introducing grooves on the lower wall of the junctions, while the upper wall had a smooth surface. Five different bifurcation angles were used in the present study: 0, 30, 45, 60, and 90 degrees. The shock tube driver pressure was P4 = 12 bar, and the pressure within the shock tube driven section, P1, was atmospheric. Air was used as the driver and driven gas. High-speed schlieren photography, using the Shimadzu Hyper-Vision camera, was used to visualise the flow-field generated by the propagating incident shock wave. The interval between each frame was of 4 μs. Pressure measurements were taken to quantify the attenuation of the incident shock wave at the exit of the different junctions. Copyright © 2009 by Gongora-Orozco Nalleli.
|Title of host publication||47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition|AIAA Aerosp. Sci. Meet. New Horiz. Forum Aerosp. Expos.|
|Publication status||Published - 2009|
|Event||47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL|
Duration: 1 Jul 2009 → …
|Conference||47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition|
|Period||1/07/09 → …|
- AIAA 2009-327