Ablative materials are commonly used to protect the nozzle metallic housing and to provide
the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because …

In this study, mathematical formulations to model charring ablation problems were
numerically implemented using finite element analysis (FEA) with ABAQUS, which account …

Nozzle throat erosion in hybrid rocket engines is generally more emphasized than in solid
rockets due to a greater concentration of oxidizing species in the combustion products …

A predictive numerical approach, based on Reynolds-averaged Navier–Stokes simulations
including the effects of turbulence, chemistry, fluid/surface interaction, and radiation, has …

Ground testing of ablative materials aims at providing critical data on the material behavior
under hypersonic reentry conditions. This is normally done in plasma wind tunnel facilities …

Numerical simulations of the flowfield in a gaseous oxygen/hydroxyl-terminated
polybutadiene hybrid rocket engine are carried out with a Reynolds-averaged Navier …

Accurate prediction of the gas-surface interaction during spacecraft reentry remains a
challenging problem for thermal protection system design. Attempts to model the surface …

Mechanical failure of graphite nozzle throats is a common problem of rocket engines. The
extreme operating conditions constitute the main cause of the problem, resulting in thermal …

Next generation spacecraft will bring back heavier payloads from explored planets. Advance
in the modeling of the thermo-chemical ablation of carbon-based thermal protection system …

Ablative materials are commonly used to protect the nozzle metallic housing and to provide
the internal contour to expand the exhaust gases in solid rocket motors. Because of the …