The Air Force Office of Scientific Research (AFOSR) has sponsored the Boundary Layer Transition (BOLT) Experiments to investigate hypersonic boundary layer transition on a low-curvature, concave surface with swept leading edges. This paper provides a review of aerothermodynamic ground test contributions by NASA Langley Research Center to the design of the BOLT flight experiment. Several test entries into the Langley Aerothermodynamics Laboratory 20-Inch Mach 6 Air Tunnel are discussed. Global surface heating distributions on subscale BOLT models were measured using either phosphor thermography or infrared thermography at a range of model attitudes and freestream Reynolds numbers. An initial test entry provided the first experimental measurements of transition on the BOLT geometry. A second test entry investigated the effects of distributed surface roughness along the swept leading edges. A third test entry provided an evaluation of the aeroheating environment on the aerodynamic fairings and a portion of the flight vehicle downstream of the BOLT experiment. These entries were intended to support the development and design of flight hardware and instrumentation for the BOLT flight experiment.


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    Titel :

    NASA Langley Aerothermodynamic Ground Tests in Support of the Boundary Layer Transition (BOLT) Flight Experiment


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    02.09.2020




    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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