@inproceedings{
 title = {DNS of Hypersonic Turbulent Boundary Layers},
 type = {inproceedings},
 year = {2004},
 publisher = {AIAA Paper 2004-2337},
 id = {e599d1ac-bb49-30ec-85c0-a471638df37b},
 created = {2021-11-12T22:38:32.129Z},
 accessed = {2021-11-12},
 file_attached = {false},
 profile_id = {6476e386-2170-33cc-8f65-4c12ee0052f0},
 group_id = {5a9f751c-3662-3c8e-b55d-a8b85890ce20},
 last_modified = {2021-11-12T22:39:55.637Z},
 read = {false},
 starred = {false},
 authored = {false},
 confirmed = {false},
 hidden = {false},
 citation_key = {martin:fdc:2004},
 private_publication = {false},
 abstract = {We present a direct numerical simulation database of supersonic and hypersonic turbu- lent boundary layers. The systematic procedure for initializing the turbulent flow fields at controlled Mach number and Reynolds number conditions is described. It is shown that simulation transients are less than 10% of the time required for gathering statistical data of the turbulent flows. The experimental conditions of Debiffeve1,2 and Elena 3,4 are sim- ulated. The magnitude of velocity and temperature fiuctuations, as well as the turbulent shear stresses given by the direct numerical simulations are in excellent agreement with the experimental data. Using the direct numerical simulation database we perform paramet- ric studies varying freestream Mach number in the range of 3 to 8 and wall-temperature condition for wall-to-freestream-temperature ratio of 2 to 5.5. © 2004 by the American Institute of Aeronautics and Astronautics, Inc.},
 bibtype = {inproceedings},
 author = {Martin, M. Pino},
 doi = {10.2514/6.2004-2337},
 booktitle = {34th AIAA Fluid Dynamics Conference}
}

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