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.


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    Titel :

    Boundary Layer Transition Correlations and Aeroheating Predictions for Mars Smart Lander


    Beteiligte:
    B. R. Hollis (Autor:in) / D. S. Liechty (Autor:in)

    Erscheinungsdatum :

    2002


    Format / Umfang :

    13 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Aeroheating Environments for a Mars Smart Lander

    Edquist, Karl / Liechty, Derek / Hollis, Brian et al. | AIAA | 2002


    Aeroheating Environments for a Mars Smart Lander

    Karl Edquist / Derek Liechty / Brian Hollis et al. | AIAA | 2006