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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Subsonic and Transonic Wind Tunnel Testing of Two Inflatable Aerodynamic Decelerators


    Contributors:

    Conference:

    International Planetary Probe Workshop 2010 ; 2010 ; Barcelona, Spain


    Publication date :

    2010-06-14


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Oscillation of Supersonic Inflatable Aerodynamic Decelerators at Mars

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


    Estimating Minimum Inflation Presusre for Inflatable Aerodynamic Decelerators

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


    Estimating Minimum Inflation Pressure for Inflatable Aerodynamic Decelerators

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