The Study Of Aerodynamic Ablation And Interior Heat Transfer For Hypersonic Aerocraft

In this dissertation, the aerodynamic ablation and interior heat transfer for hypersonic aerocraft are studied. As an example, the shape distortion of the certain projectile due to ablating effects and the process of heat transfer are numerically simulated. The following results are obtained:1. Melting ablation model is used in the computation, and the melting point of WO3 is considered as the ablation rules. From the charts of the shape distortion of the projectile, it is found that the results are compared well with experimental data.2. Dynamic grid method is applied to solve mesh distortion resulting from the aerodynamic ablation of the projectile. With the temperature distribution around the projectile, the relation of flying velocity and ablation is analyzed.3. Fluid-solid coupling analysis method is used to study the whole system which regards the interactive solid parts and fluid parts as an integrated system, and transforms outer boundary condition to inner boundary condition, and then the coupling problems of fluid heat transfer and solid heat penetration are solved. So that more exact results are obtained and heat transfer simulation becomes more reasonable and simpler.4. Turbulence model and radiation model are added in the computation, so the influence of viscosity and radiate is considered, and more actual results for fluid and more accurate temperature are obtained.5. Based on the accurate simulation of projectile flow field, the aerodynamic ablation is computed with different velocity to conclude the rules of ablation. At last, the interior temperature distribution is analyzed.