Recent shock tunnel experiments have shown an increase in transition Reynolds number with increasing freestream total enthalpy, and linear stability theory has been used to reproduce the same trends. It was observed that as the freestream enthalpy is increased, the presence of chemical reactions and translational-vibrational energy exchange in the boundary layer becomes increasingly important and a stability code which does not take these effects into account will not give correct disturbance amplification rates. Previous work has shown a significant damping effect of endothermic chemical reactions and thermal energy transfer in boundary layer disturbances. Conversely, exothermic reactions were shown to have a destabilizing effect. These results were observed while simulating the complicated air flows of the shock tunnel experiments, making it difficult to effectively isolate the relevant stabilizing or destabilizing mechanisms. Therefore, a series of numerical experiments were performed under more controlled conditions in an attempt to further our understanding of the role of thermochemical interactions in hypersonic boundary layer stability.
|Original language||English (US)|
|Number of pages||12|
|State||Published - 1998|
|Event||29th AIAA Fluid Dynamics Conference - Albuquerque, United States|
Duration: Jun 15 1998 → Jun 18 1998
|Other||29th AIAA Fluid Dynamics Conference|
|Period||6/15/98 → 6/18/98|
Bibliographical noteFunding Information:
and AASERT Grant No. DA/DAAH04-96-1-0269. This work was also sponsored in part by the Army High Performance Computing Research Center under the auspices of the Department of the Army, Army Research Laboratory cooperative agreement number DAAH04-95-2-0003 / contract number DAAH04-95-C-0008, the content of which does not necessarily re- flect the position or the policy of the government, and no official endorsement should be inferred.
© 1998, American Institute of Aeronautics and Astronautics, Inc.
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