Mesh Adaptation for Simulating Lateral Jet Interaction Flow
Abstract
:1. Introduction
2. Hybrid Mesh Adaptive Method
2.1. Numerical Simulation Method
2.2. Adaptation Strategy
2.3. Adaptive Criteria
2.3.1. Quasi-Gradient-Based Adaptation Criterion
2.3.2. Adaptation Criterion Based on Curl and Gradient of Velocity
2.3.3. Adaptation Criterion Based on Vortex Vector
2.4. Combined Adaptation Criteria
- (1)
- If a mesh cell satisfies and , then it needs to be refined. This identifies shock waves in the flow field.
- (2)
- If a mesh cell satisfies or , then it needs to be refined. This identifies vortex structures in the flow field.
- (3)
- If a mesh cell satisfies or , then it needs to be coarsened. This identifies absence of shock waves in the flow field.
- (4)
- If a mesh cell satisfies and , then it needs to be coarsened. This identifies absence of a vortex in the flow field.
2.5. Frequency Selection for Dynamic Grid Adaptation
3. Adaptive Simulation of Lateral Jet Interaction Flow Field
3.1. Generic Missile Model and Flow Conditions
3.2. Transverse Jet Efficiency
3.3. Simulation of a Steady Flow
3.4. Simulation of an Unsteady Flow
4. Summary
- (1)
- A combined adaptation criterion for unstructured hybrid mesh is proposed for simulating lateral jet interaction flows. This can effectively capture complex structures in the lateral jet interaction flow field, such as shock waves and vortices.
- (2)
- The proposed adaptation criterion can significantly improve convergence of flow computation and resolution of flow structures. It also plays an important role in numerical simulation of lateral jet interaction flows and improves prediction accuracy of the aerodynamic characteristics of a missile.
- (3)
- Compared to the uniformly refined mesh, the adaptive mesh had a similar resolution to the flow field, while the total number of mesh cells was much smaller. Additionally, in this way, computational efficiency can be improved greatly.
- (4)
- The present adaptation criteria can identify characteristic structures in the unsteady flow field and effectively improve resolution of flow and accuracy of aerodynamic calculation.
- (5)
- In parallel computing, adaptive refined mesh may be concentrated in one processor in such a way that seriously imbalanced distributed mesh cannot reduce computational cost effectively. Implementation of dynamic load balancing in the solver for parallel computing will be the focus of future research.
Author Contributions
Funding
Data Availability Statement
Acknowledgments
Conflicts of Interest
References
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Mesh Adaptation | Total Number of Mesh Cells | Growth Rate |
---|---|---|
Base mesh | 1.71 million | / |
Once-adapted | 4.32 million | 155.5% |
Twice-adapted | 14.22 million | 731.6% |
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Tian, S.; Peng, Z. Mesh Adaptation for Simulating Lateral Jet Interaction Flow. Aerospace 2022, 9, 781. https://doi.org/10.3390/aerospace9120781
Tian S, Peng Z. Mesh Adaptation for Simulating Lateral Jet Interaction Flow. Aerospace. 2022; 9(12):781. https://doi.org/10.3390/aerospace9120781
Chicago/Turabian StyleTian, Shuling, and Zongzi Peng. 2022. "Mesh Adaptation for Simulating Lateral Jet Interaction Flow" Aerospace 9, no. 12: 781. https://doi.org/10.3390/aerospace9120781