Mach 10 Bow Shock and Gas-Cap Unsteadiness Measurements Using Rayleigh Scattering
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia 23681
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.J054724
Reference32 articles.
1. Free-stream density perturbations in a reflected-shock tunnel
2. BounitchA.LewisD. R.LaffertyJ. F. “Improved Measurements of ‘Tunnel Noise’ Pressure Unsteadiness in the AEDC Hypervelocity Wind Tunnel No. 9,” AIAA Paper 2011-1200, 2011.
3. Pressure Fluctuation Measurements in the NASA Langley 20-Inch Mach 6 Wind Tunnel
4. ICASE/NASA LaRC Series;Bushnell D.
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1. High-Speed Schlieren Analysis of Retropropulsion Jet in Mach 10 Flow;Journal of Spacecraft and Rockets;2020-01
2. Gas density field imaging in shock dominated flows using planar laser scattering;Experiments in Fluids;2018-06-05
3. Mach 10 Bow-Shock Unsteadiness Modeled by Linear Combination of Two Mechanisms;AIAA Journal;2017-12
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