Abstract
This paper describes a computational method for the analysis and mitigation via shape optimization of the sonic boom associated with supersonic flight. The method combines a CFD approach for determining the near-field pressure field and an acoustic scheme for predicting the initial shock pressure rise at the ground. Two venues are considered for computing the ground signature. The performance of both approaches is evaluated using flight test data of two different configurations of an F5 fighter aircraft.
| Original language | English |
|---|---|
| Pages (from-to) | 217-243 |
| Number of pages | 27 |
| Journal | European Journal of Computational Mechanics |
| Volume | 17 |
| Issue number | 1-2 |
| DOIs | |
| Publication status | Published - 2008 |
Funding
The first author acknowledges the support of the National Science Foundation under grant DMI-0348759. The opinions and conclusions presented in this paper are those of the authors and do not necessarily reflect the views of the sponsoring organization.
| Funders | Funder number |
|---|---|
| National Science Foundation | DMI-0348759 |
Keywords
- Adjoint method
- Ray tracing
- Shape optimization
- Sonic boom