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Boundary layer transition correlations and aeroheating predictions for mars smart lander
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hollis, Brian R. Liechty, Derek S. |
| Copyright Year | 2002 |
| Description | Laminar and turbulent perfect-gas air, Navier-Stokes computations have been performed for a proposed Mars Smart Lander entry vehicle at Mach 6 over a free stream Reynolds number range of 6.9 x 10(exp 6/m to 2.4 x 10(exp 7)m(2.1 x 10(exp 6)/ft to 7.3 x 10(exp 6)ft) for angles-of-attack of 0-deg, 11-deg, 16-deg, and 20-deg, and comparisons were made to wind tunnel heating data obtained at the same conditions. Boundary layer edge properties were extracted from the solutions and used to correlate experimental data on the effects of heat-shield penetrations (bolt-holes where the entry vehicle would be attached to the propulsion module during transit to Mars) on boundary-layer transition. A non-equilibrium Martian-atmosphere computation was performed for the peak heating point on the entry trajectory in order to determine if the penetrations would produce boundary-layer transition by using this correlation. |
| File Size | 1396769 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030006678 |
| Archival Resource Key | ark:/13960/t9v170d4b |
| Language | English |
| Publisher Date | 2002-01-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Thermodynamics Navier-stokes Equation Correlation Turbulence Temperature Effects Reynolds Number Aerodynamic Heating Wind Tunnel Tests Ideal Gas Boundary Layer Transition Trajectories Angle of Attack Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
