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Computational aerothermodynamics in aeroassist applications
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gnoffo, Peter A. |
| Copyright Year | 2001 |
| Description | Aeroassisted planetary entry uses atmospheric drag to decelerate spacecraft from super-orbital to orbital or suborbital velocities. Numerical simulation of flow fields surrounding these spacecraft during hypersonic atmospheric entry is required to define aerothermal loads. The severe compression in the shock layer in front of the vehicle and subsequent, rapid expansion into the wake are characterized by high temperature, thermo-chemical nonequilibrium processes. Implicit algorithms required for efficient, stable computation of the governing equations involving disparate time scales of convection, diffusion, chemical reactions, and thermal relaxation are discussed. Robust point-implicit strategies are utilized in the initialization phase; less robust but more efficient line-implicit strategies are applied in the endgame. Applications to ballutes (balloon-like decelerators) in the atmospheres of Venus, Mars, Titan, Saturn, and Neptune and a Mars Sample Return Orbiter (MSRO) are featured. Examples are discussed where time-accurate simulation is required to achieve a steady-state solution. |
| File Size | 884650 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20010071532 |
| Archival Resource Key | ark:/13960/t4vj0gw51 |
| Language | English |
| Publisher Date | 2001-01-19 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Algorithms Drag Aeroassist Flow Distribution Chemical Reactions Computerized Simulation Atmospheric Entry Thermal Stresses Aerothermodynamics Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
