Carbon Dioxide Injection for Hypervelocity Boundary Layer Stability
Abstract
An approach for introducing carbon dioxide as a means or stabilizing a hypervelocity boundary layer over a slender bodied vehicle is investigated through the use of numerical simulations. In the current study, two different test bodies are examined. The first is a five-degree-half-angle cone currently under research at the GALCIT T5 Shock Tunnel with a 4 cm porous wall insert used to transpire gas into the boundary layer. The second test body is a similar cone with a porous wall over a majority of cone surface. Computationally, the transpiration is performed using an axi-symmetric flow simulation with wall-normal blowing. The effect of the injection and the transition location are gauged by solving the parabolized stability equations and using the semi-empirical e^N method. The results show transition due to the injection for the first test body and a delay in the transition location for the second test body as compared to a cone without injection under the same flight conditions. The mechanism for the stabilizing effect of carbon dioxide is also explored through selectively applying non-equilibrium processes to the stability analysis. The results show that vibrational non-equilibrium plays a role in reducing disturbance amplification; however, other factors also contribute.
Additional Information
© 2010 by Ross Wagnild. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission.Attached Files
Accepted Version - AIAA-2010-1244.pdf
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Additional details
- Eprint ID
- 99296
- Resolver ID
- CaltechAUTHORS:20191016-100220993
- Created
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2019-10-16Created from EPrint's datestamp field
- Updated
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2021-11-16Created from EPrint's last_modified field
- Caltech groups
- GALCIT
- Other Numbering System Name
- AIAA Paper
- Other Numbering System Identifier
- 2010-1244