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    Current wind tunnel capability and planned improvements at Lewis Research Center (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NASA Lewis 8 x 6-ft and 10 x 10-ft supersonic wind tunnels furnish the capability for propulsion system tests in the Mach 0.4-3.5 range; the 9 x 15-ft wind tunnel at the facility addresses propulsion installation problems at the lower, takeoff and landing speeds, further providing an excellent anechoic environment in which to measure propeller and fan noise. The NASA Lewis Icing Research Tunnel is the largest of its kind in the free world. The currently mothballed Hypersonic Tunnel Facility could furnish the best available simulations of nonvitiated Mach 5-7 test conditions. Studies are underway to identify prospective performance-enhancing modifications for these facilities in the 1990s and beyond.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 86-0728
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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