Abstract
Direct Numerical Simulation is being used to study cross flow instabilities on the Hyper- sonic International Flight Research Experimentation program flight 5 vehicle. The simulations replicate a 38.1% scale model at the 1090 kPa flight conditions used for experiments at the Boeing/AFOSR Mach 6 Quiet Tunnel. In this paper special attention is given to the development of a base flow for the problem. Due to the extreme sensitivity of cross flow instability, disturbances are seeded very easily and can pollute the base ow. Several com- putations designed to limit this phenomenon while still resolving the mean flow physics are presented. A simulation of a quarter of the HIFiRE{5 forebody with 216 million elements is being performed. Once completed, the development and breakdown of cross flow vortices will be analyzed, with attention given to spanwise wavenumber evolution, nonlinear interaction and modification of the mean flow, and the fostering of secondary instabilities.
| Original language | English (US) |
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| Title of host publication | 53rd AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Print) | 9781624103438 |
| DOIs | |
| State | Published - 2015 |
| Event | 53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States Duration: Jan 5 2015 → Jan 9 2015 |
Publication series
| Name | 53rd AIAA Aerospace Sciences Meeting |
|---|
Other
| Other | 53rd AIAA Aerospace Sciences Meeting, 2015 |
|---|---|
| Country/Territory | United States |
| City | Kissimmee |
| Period | 1/5/15 → 1/9/15 |
Bibliographical note
Publisher Copyright:© 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.