Feasibility study, carried out at University of Minnesota, is concerned with basic principles for design of supersonic parachute; analysis is based on shock wave patterns and area ratios related to supersonic diffuser inlet theory; several aerodynamic principles are postulated and explored which in connection with related combination of solid cone and flexible canopy lead to development of aerodynamic decelerator, called Supersonic Guide Surface Parachute.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Supersonic parachute based on inlet diffuser concept


    Additional title:

    AGARD -- Report


    Contributors:

    Published in:

    Publication date :

    1963


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    FEASIBILITY STUDY OF SHORT SUBSONIC DIFFUSER CONCEPT FOR SUPERSONIC INLET

    Miki, H. / Akatsuka, J. / Kikura, I. et al. | British Library Conference Proceedings | 2022


    ENGINE INLET AIR DIFFUSER CONTROLS FOR SUPERSONIC AIRCRAFT

    HERMANN, RUDOLF | SAE Technical Papers | 1956


    Engine inlet air diffuser controls for supersonic aircraft

    Hermann, R. | Engineering Index Backfile | 1956


    Supersonic Parachute Aerodynamic Testing

    Lingard, J.S. / Underwood, J.C. / Marraffa, L. et al. | British Library Conference Proceedings | 2013