Flow visualization in a cryogenic wind tunnel using holography
Alpheus W. Burner, William K. Goad, 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, 1982 - Technology & Engineering - 22 pages
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0.3-Meter Transonic Cryogenic 1/T and p/T 122-cm focal length airfoil aluminum box angle of attack beam splitter beam was directed Burner and W. K. caused by temperature Changes in density collimated conjugate reference beam CONJUGATE SCENE BEAM D-shaped density fluctuations appear disturbance diverging scene beam emphasize the shock experimental arrangement flow field focus Focused on tubing focused shadowgraph geometry graininess hologram plane holographic reconstruction independent of tunnel interferometry irradiance knife edge Langley 0.3-Meter Transonic Langley Research Center Mach number NASA optical power parabolic mirror Performing Organization photodiode pinhole plane wave plate plenum plotted against 1/T pressure fluctuations pressure range range from 1.1 reconstructed beam reconstructed scene beam reference fringes reflector refractive index ruby laser schlieren photograph setup shadowgraph effect spatial spatial filter spot spot size temperature fluctuations test section test-section Transonic Cryogenic Tunnel tunnel conditions tunnel tests variations WAVE FRONTS wavelength wedge angle