Statistics – Computation
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002stin...0305808h&link_type=abstract
Conference Paper, 32nd AIAA Fluid Dynamics Conference and Exhibit
Statistics
Computation
Boundary Layer Transition, Correlation, Aerodynamic Heating, Mars Atmosphere, Landing, Temperature Effects, Angle Of Attack, Computation, Heat Shielding, Hypersonic Speed, Navier-Stokes Equation, Propulsion, Reynolds Number
Scientific paper
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 106/m to 2.4 x 107/m (2.1 x 106/ft to 7.3 x 106)/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 a t 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.
Hollis Brian R.
Liechty Derek S.
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