Abstract
We propose new global artificial boundary conditions (ABCs) for computation of flows with propulsive jets. The algorithm is based on application of the difference potentials method (DPM). Previously, similar boundary conditions have been implemented for calculation of external compressible viscous flows around finite bodies. The proposed modification substantially extends the applicability range of the DPM-based algorithm. We present the general formulation of the problem, describe our numerical methodology, and discuss the corresponding computational results. The particular configuration that we analyze is a slender three-dimensional body with boat-tail geometry and supersonic jet exhaust in a subsonic external flow under zero angle of attack. Similar to the results obtained earlier for the flows around airfoils and wings, current results for the jet flow case corroborate the superiority of the DPM-based ABCs over standard local methodologies from the standpoints of accuracy, overall numerical performance, and robustness.
Original language | English |
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Pages (from-to) | 2014-2022 |
Number of pages | 9 |
Journal | AIAA Journal |
Volume | 38 |
Issue number | 11 |
DOIs | |
Publication status | Published - Nov 2000 |
Externally published | Yes |
ASJC Scopus subject areas
- Aerospace Engineering