Abstract
A hybrid grid approach has been developed for the simulation of next generation heavy-lift space vehicles in the launch environment. The motivation for the hybrid method is to reduce the turn-around time of computational fluid dynamic simulations and improve the ability to handle complex geometry and flow physics. The LAVA (Launch Ascent and Vehicle Aerodynamics) hybrid scheme, consists of two solvers: An off-body immersed-boundary Cartesian solver with block-structured adaptive mesh refinement and a near-body unstructured body-fitted solver which includes conjugate heat transfer. Two-way coupling is achieved through overset connectivity between the off-body and near-body grids. This work seeks to determine the best practices of the individual flow solvers, perform verification with code-to-code comparisons and validation using flight data. Representative unsteady 2D trench and 3D Space Shuttle (STS-135) test cases are used in the analysis.
| Original language | English |
|---|---|
| State | Published - 2012 |
| Event | 7th International Conference on Computational Fluid Dynamics, ICCFD 2012 - Big Island, United States Duration: Jul 9 2012 → Jul 13 2012 |
Conference
| Conference | 7th International Conference on Computational Fluid Dynamics, ICCFD 2012 |
|---|---|
| Country/Territory | United States |
| City | Big Island |
| Period | 7/9/12 → 7/13/12 |
Bibliographical note
Publisher Copyright:© 2012 7th International Conference on Computational Fluid Dynamics, ICCFD 2012. All rights reserved.
Keywords
- Adaptive mesh refinement
- Cartesian methods
- Computational fluid dynamics
- Hybrid grid methodologies
- Immersed-boundary
- Overset
- Unstructured
ASJC Scopus subject areas
- Energy Engineering and Power Technology
- Aerospace Engineering
- Computational Mechanics
- Mechanical Engineering
- Mechanics of Materials
- Condensed Matter Physics