@article{
 title = {Thermoacoustic loads and fatigue of hypersonic vehicle skin panels},
 type = {article},
 year = {1993},
 keywords = {Acoustic Vibrations,Airbreathing Hypersonic Vehicle,Blended Wing Body,Bow Shock,Finite Element Dynamic Analysis,Heat Flux,Hypersonic Vehicles,Laminar Turbulent Transition,Overall Sound Pressure Level,Transient Thermal Analysis},
 pages = {971-978},
 volume = {30},
 month = {5},
 day = {22},
 id = {df9fa254-e09c-31c5-8e9e-af888abffddf},
 created = {2021-10-28T20:58:25.611Z},
 accessed = {2021-10-28},
 file_attached = {true},
 profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},
 group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},
 last_modified = {2021-10-28T20:58:26.187Z},
 read = {false},
 starred = {false},
 authored = {false},
 confirmed = {false},
 hidden = {false},
 citation_key = {blevins:ja:1993},
 private_publication = {false},
 abstract = {A thermo-vibro-acoustic analysis of skin panels for airbreathing hypersonic vehicles is made for a generic trajectory and vehicle design. Aerothermal analysis shows that impingement of the bow shock wave on the vehicle produces fluctuating pressures, and local heat fluxes greatly exceed those due to the attached turbulent boundary. Thermal analysis of carbon-carbon skin panels shows that maximum temperatures will exceed 2700°F (1480°C) at the top of the ascent trajectory. Engine acoustic analysis indicates that sound levels will exceed 170 dB. As a result, loads due to engine acoustics and shock impingement dominate the design of many transatmospheric vehicle skin panels. © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.},
 bibtype = {article},
 author = {Blevins, Robert D. and Holehouse, Ian and Wentz, Kenneth R.},
 doi = {10.2514/3.46441},
 journal = {Journal of Aircraft},
 number = {6}
}

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Aerothermal analysis shows that impingement of the bow shock wave on the vehicle produces fluctuating pressures, and local heat fluxes greatly exceed those due to the attached turbulent boundary. Thermal analysis of carbon-carbon skin panels shows that maximum temperatures will exceed 2700°F (1480°C) at the top of the ascent trajectory. Engine acoustic analysis indicates that sound levels will exceed 170 dB. As a result, loads due to engine acoustics and shock impingement dominate the design of many transatmospheric vehicle skin panels. © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.","bibtype":"article","author":"Blevins, Robert D. and Holehouse, Ian and Wentz, Kenneth R.","doi":"10.2514/3.46441","journal":"Journal of Aircraft","number":"6","bibtex":"@article{\n title = {Thermoacoustic loads and fatigue of hypersonic vehicle skin panels},\n type = {article},\n year = {1993},\n keywords = {Acoustic Vibrations,Airbreathing Hypersonic Vehicle,Blended Wing Body,Bow Shock,Finite Element Dynamic Analysis,Heat Flux,Hypersonic Vehicles,Laminar Turbulent Transition,Overall Sound Pressure Level,Transient Thermal Analysis},\n pages = {971-978},\n volume = {30},\n month = {5},\n day = {22},\n id = {df9fa254-e09c-31c5-8e9e-af888abffddf},\n created = {2021-10-28T20:58:25.611Z},\n accessed = {2021-10-28},\n file_attached = {true},\n profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},\n group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},\n last_modified = {2021-10-28T20:58:26.187Z},\n read = {false},\n starred = {false},\n authored = {false},\n confirmed = {false},\n hidden = {false},\n citation_key = {blevins:ja:1993},\n private_publication = {false},\n abstract = {A thermo-vibro-acoustic analysis of skin panels for airbreathing hypersonic vehicles is made for a generic trajectory and vehicle design. Aerothermal analysis shows that impingement of the bow shock wave on the vehicle produces fluctuating pressures, and local heat fluxes greatly exceed those due to the attached turbulent boundary. Thermal analysis of carbon-carbon skin panels shows that maximum temperatures will exceed 2700°F (1480°C) at the top of the ascent trajectory. Engine acoustic analysis indicates that sound levels will exceed 170 dB. As a result, loads due to engine acoustics and shock impingement dominate the design of many transatmospheric vehicle skin panels. © 1992 by the American Institute of Aeronautics and Astronautics, Inc. 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