摘要 :
A novel approach for modeling hypersonic flow fields and material response in a coupled manner is developed and demonstrated in this work. The procedure leverages modern programming techniques such as application programming inter...
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A novel approach for modeling hypersonic flow fields and material response in a coupled manner is developed and demonstrated in this work. The procedure leverages modern programming techniques such as application programming interface to create minimally intrusive pathways of communication between solvers while tightly coupling physics of both domains. With the intent of capturing the multi-physical nature of reentry problems, three main capabilities are developed: conjugate heat transfer methodology between US3D (flow solver) and Icarus (material response solver); implementation of a high-fidelity air-carbon ablation model for modeling gas-surface interactions; and a robust mesh motion algorithm to capture both solid and fluid domain deformations due to ablation. A demonstration of this development is presented on an ablating blunt cone geometry.
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摘要 :
A novel approach for modeling hypersonic flow fields and material response in a coupled manner is developed and demonstrated in this work. The procedure leverages modern programming techniques such as application programming inter...
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A novel approach for modeling hypersonic flow fields and material response in a coupled manner is developed and demonstrated in this work. The procedure leverages modern programming techniques such as application programming interface to create minimally intrusive pathways of communication between solvers while tightly coupling physics of both domains. With the intent of capturing the multi-physical nature of reentry problems, three main capabilities are developed: conjugate heat transfer methodology between US3D (flow solver) and Icarus (material response solver); implementation of a high-fidelity air-carbon ablation model for modeling gas-surface interactions; and a robust mesh motion algorithm to capture both solid and fluid domain deformations due to ablation. A demonstration of this development is presented on an ablating blunt cone geometry.
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摘要 :
1. FFCFD continues to expand V&V efforts with focus on low supersonic/transonic flow 1.1 Development of reduced DoF analysis with FFCFD enables fast population of Mach-alpha aero-database 1.2 Orion CM "cross-facility" comparison shows good agreement between simulation predicted pitch damping and experimental results 2. FFCFD support for DragonFly, EES, SpaceX Dragon Capsule 2.1 Application of end-to-end dynamic stability assessment using 1 -DoF simulations have been carried out for a range of Mach numbers and initial AoAs....
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1. FFCFD continues to expand V&V efforts with focus on low supersonic/transonic flow 1.1 Development of reduced DoF analysis with FFCFD enables fast population of Mach-alpha aero-database 1.2 Orion CM "cross-facility" comparison shows good agreement between simulation predicted pitch damping and experimental results 2. FFCFD support for DragonFly, EES, SpaceX Dragon Capsule 2.1 Application of end-to-end dynamic stability assessment using 1 -DoF simulations have been carried out for a range of Mach numbers and initial AoAs.
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