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Heat transfer measurements were made in a Mach 6 low disturbance wind tunnel to quantify boundary-layer transition on the BOLT flight vehicle geometry. Natural transition was measured for the first time and comparisons were made to flight test data from the BOLT-II flight test campaign.
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This page is a summary of: Boundary-Layer Transition on BOLT in High Reynolds Number Mach-6 Quiet Flow, Journal of Spacecraft and Rockets, July 2025, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.a36425.
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