Research to develop high-speed airbreathing aerospace propulsion systems was underway in the late 1950s. A major part of the effort involved the supersonic combustion ramjet, or scramjet, engine. Work had also begun to develop computational techniques for solving the equations governing the flow through a scramjet engine. However, scramjet technology and the computational methods to assist in its evolution would remain apart for another decade. The principal barrier was that the computational methods needed for engine evolution lacked the computer technology required for solving the discrete equations resulting from the numerical methods. Even today, computer resources remain a major pacing item in overcoming this barrier. Significant advances have been made over the past 35 years, however, in modeling the supersonic chemically reacting flow in a scramjet combustor. To see how scramjet development and the required computational tools finally merged, we briefly trace the evolution of the technology in both areas.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Methods for Prediction of High-Speed Reacting Flows in Aerospace Propulsion


    Contributors:

    Published in:

    Publication date :

    2014-03-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English