The objective of this work was to develop new engineering correlations for stagnation point aeroheating for Mars entry vehicles. New convective and radiative heating relations have been formulated over a wide range of entry conditions. These relations have been formulated using information from recent experimental testing and modeling enhancements. The new correlations are compared to existing relations commonly used in engineering design and analysis. Finally the correlations are tested by applying them to the Mars Pathfinder entry trajectory to demonstrate their applicability. These new correlations are a significant improvement over existing relations in terms of the accuracy, domain of applicability, and the captured physics.


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    Titel :

    Updated Stagnation Point Aeroheating Correlations for Mars Entry


    Beteiligte:
    Brandis, A. M. (Autor:in)

    Kongress:

    2018 AIAA Aviation ; 2018 ; Atlanta, GA, United States


    Erscheinungsdatum :

    25.06.2018


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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