Inviscid flow fields have been computed for blunt axisymmetric shapes exposed to a hypersonic environment. A fully implicit scheme using a flux vector splitting technique was used to obtain a finite difference formulation. To increase computational efficiency, an approximate factorization scheme was used. Flow-field solutions were obtained for chemically reacting air using a decoupled approach. Flow fields were computed for blunted, flared shapes over a range of Mach numbers from 2 to 20.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Inviscid Flow Field Computation of Hypervelocity Projectiles


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Technology Conference and Exposition ; 1988



    Publication date :

    1988-10-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    A Novel Telemetry System for Hypervelocity Projectiles

    Grumann, H. / Zimmermann, G. / IEEE | British Library Conference Proceedings | 1995