SUMMARY
This discussion focuses on accurately modeling atmospheric pressure at altitudes up to 300 km, particularly for a vehicle in descent after being launched by a rocket. The user has successfully modeled pressure up to 50 km using the equation p-p1 = rho*v^2*sin^2theta, with p1 defined as p0(1-(L*h/T0))^(g*M/R*L). However, they seek guidance on assumptions for altitudes above 50 km, where traditional models become complex and computational fluid dynamics (CFD) may be necessary. Key resources include NASA's atmospheric models and the NRLMSISE-00 model for further exploration.
PREREQUISITES
- Understanding of fluid dynamics principles
- Familiarity with Python for modeling
- Knowledge of atmospheric pressure equations
- Basic concepts of computational fluid dynamics (CFD)
NEXT STEPS
- Research NASA's atmospheric models for altitudes above 50 km
- Explore the NRLMSISE-00 model for atmospheric density and pressure calculations
- Learn about computational fluid dynamics (CFD) techniques for high-altitude modeling
- Investigate the impact of temperature and altitude on atmospheric pressure
USEFUL FOR
Aerospace engineers, researchers in atmospheric science, and developers working on high-altitude vehicle simulations will benefit from this discussion.