Two inflatable aerodynamic decelerator designs were tested in the Transonic Dynamics Tunnel at the NASA Langley Research Center: a tension cone and an isotensoid. The tension cone consists of a flexible tension shell attached to a torus and the isotensoid employs a ram-air inflated envelope. Tests were conducted at Mach numbers from 0.3 to 1.08 and Reynolds numbers from 0.59 to 2.46 million. The main objective of these tests was to obtain static aerodynamic coefficients at subsonic and transonic speeds to supplement supersonic aerodynamic data for these same two designs. The axial force coefficients of both designs increased smoothly from subsonic through transonic Mach numbers. Dynamic data show significant oscillation of the tension cone and minimal oscillation of the isotensoid. The transonic and subsonic data will be used to assemble an inflatable decelerator aerodynamic database for use in computational analyses and system studies.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Subsonic and Transonic Wind Tunnel Testing of Two Inflatable Aerodynamic Decelerators


    Beteiligte:

    Kongress:

    International Planetary Probe Workshop 2010 ; 2010 ; Barcelona, Spain


    Erscheinungsdatum :

    2010-06-14


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Oscillation of Supersonic Inflatable Aerodynamic Decelerators at Mars

    Smith, Brandon / Hill, Jeremy / Clark, Ian et al. | AIAA | 2011


    Oscillation of Supersonic Inflatable Aerodynamic Decelerators at Mars

    Smith, B. / Hill, J. / Clark, I. et al. | British Library Conference Proceedings | 2011


    Estimating Minimum Inflation Presusre for Inflatable Aerodynamic Decelerators

    Brown, G. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2009