Equilibrium shape change
Abstract
A rapid computerized procedure for determining shape stable ablative nosetip contours in the presence of entropy layer entrainment and boundary layer transition has been developed. Turbulent spot theory was employed to describe aerodynamic heating and boundary layer mass flow in the transition region. Body surface pressures were described by modified Newtonian and Prandtl-Meyer flow relations. Continuous surface contours were then obtained by integration through a saddle-point singularity dependent upon flight Mach number and specific heat ratio. Results presented emphasize effects of surface roughness and swallowing on the development of convex/concave nose shapes.
- Publication:
-
AIAA, 13th Aerospace Sciences Meeting
- Pub Date:
- January 1975
- Bibcode:
- 1975aiaa.meetV....S
- Keywords:
-
- Ablative Nose Cones;
- Boundary Layer Transition;
- Computerized Simulation;
- Equilibrium Equations;
- Reentry Vehicles;
- Bow Waves;
- Heat Transfer;
- Laminar Flow;
- Mach Number;
- Newton Pressure Law;
- Prandtl-Meyer Expansion;
- Reynolds Number;
- Runge-Kutta Method;
- Shock Wave Profiles;
- Spacecraft Configurations;
- Specific Heat;
- Turbulent Flow;
- Fluid Mechanics and Heat Transfer