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BOLT-2 Roughness Side Flight Data Results and AnalysisThis report provides an in-depth review of the flight data obtained from Side B, also known as the roughness side, of BOLT-2, which was developed and designed to measure the effectiveness of boundary layer trips at hypersonic conditions. Three discrete-roughness trips were implemented on Side B at specific locations, with the necessary sensor layout, to investigate the flight conditions at which they no longer maintained turbulence behind them. All three trips were the same type that were scaled and sized based on predictions of local boundary layer thicknesses to provide the same level of effectiveness. One trip was on the vehicle centerline, where the boundary layer is relatively thick, while the other two were symmetrically located outboard where the boundary layer is much thinner. The relative difference in boundary layer thickness between these locations was roughly on the order of 3-to-1, thus the centerline trip was geometrically about three times larger than the outboard trips. A first order assessment of the Side B flight results is indicated by these three trips forcing transition onset at the same time during flight. The enclosed flight data shows that the performance of each individual trip was nearly identical, with allowances for minor variations attributed to measurement accuracy.
Document ID
20240015600
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Scott A Berry
(Langley Research Center Hampton, United States)
Casey J Broslawski
(Langley Research Center Hampton, United States)
Bradley M Wheaton
(Johns Hopkins University Applied Physics Laboratory North Laurel, United States)
David W Adamczak
(United States Air Force Research Laboratory Wright-Patterson AFB, United States)
Rodney Bowersox
(Texas A&M University College Station, United States)
Aaron T Dufrene
(Calspan-University of Buffalo Research Center Buffalo, New York, United States)
Date Acquired
December 5, 2024
Publication Date
December 1, 2024
Publication Information
Publisher: National Aeronautics and Space Administration
Subject Category
Fluid Mechanics and Thermodynamics
Aircraft Design, Testing and Performance
Report/Patent Number
NASA/TM-20240015600
Funding Number(s)
WBS: 725017.02.07.03.01
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Technical Review
NASA Peer Committee
Keywords
Flight Data
Boundary Layer Transition
Hypersonics
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