Holographic flow visualization at the Langley Expansion Tube
William K. Goad, Alpheus W. Burner, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1981 - Technology & Engineering - 22 pages
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acceleration gas acceleration section Argon Laser Blunt Bodies Carbon Dioxide Charles G cm in diameter cn H double-diaphragm section double-pulse interferometry driver section exited the tube External Trigger facility field of view Figure 13(a Film Back 10-cm flow field flow plate flow-visualization system free-stream density gage helium-neon alinement laser holo Holographic Flow Visualization holographic plate holographic system Hypersonic incident shock wave Infinite-fringe interferogram intermediate section km/s Langley 6-Inch Expansion Langley Expansion Tube Langley Research Center laser schlieren NASA no-flow hologram normal shock density oscilloscope photodiode primary diaphragm primary shock pulse occurred 150 radius of curvature reconstruction system reference beam reference-fringe ruby laser ruby-laser run in Langley rupture scene beam Schlieren photographs secondary diaphragm section is pressurized sensitivity adjustments shock tube shock-tube runs shows the primary Shuttle Orbiter nose speed of sound spherically blunted 80 technique test gases test section upstream expansion wave vertical knife-edge cutoff