Abstract
A steady-state, shock-induced combustion problem due to the Mach 6.46 flight of a blunt projectile in a stoichiometric hydrogen and air mixture is studied. Various mechanisms for the hydrogen-air reactions are tested to determine the impact the selection of reaction mechanism has on simulation accuracy. Characteristics of the mechanisms such as heat release rate and induction time are quantified using a zero-dimension analysis. The computed flow field is found to depend on the range of a Damkohler parameter based on the induction time behind the shock. Results suggest factors which impact induction time, such as high-pressure effects in the reaction mechanisms, are key.
| Original language | English |
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| Publication status | Published - 1998 |
| Externally published | Yes |
| Event | 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States Duration: 12 Jan 1998 → 15 Jan 1998 |
Conference
| Conference | 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 |
|---|---|
| Country/Territory | United States |
| City | Reno |
| Period | 12/01/98 → 15/01/98 |
Bibliographical note
Publisher Copyright:© 1998 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.