A method for calculating the nosetip ablation of a reentry body
Abstract
An analytical method is developed for calculating the nosetip ablation of a reentry body with allowance for variations of shape due to the ablated thickness of material, which affects the aerodynamic fluxes involved. The proposed method is limited to rotational ablation about the nosetip axis. Attention is directed to a scheme for calculating the aerodynamic fluxes on a reentry body of arbitrary shape and to a scheme for calculating material ablation. It is shown that this method must consider a variety of parameters from aerodynamic (transition, wall roughness) and ablation (wall effects) standpoints.
- Publication:
-
12th Association Aeronautique et Astronautique de France, Colloque d'Aerodynamique Appliquee
- Pub Date:
- November 1976
- Bibcode:
- 1976aaaf.coll.....P
- Keywords:
-
- Ablative Nose Cones;
- Aerodynamic Heating;
- Reentry Effects;
- Surface Roughness Effects;
- Boundary Layer Flow;
- Carbon-Carbon Composites;
- Numerical Analysis;
- Silicone Resins;
- Transition Flow;
- Turbulent Flow;
- Fluid Mechanics and Heat Transfer