Review of some of design parameters that were considered in integration of induction system, secondary air system, jet nozzle and basic turbojet gas generator for SST by General Electric Co; most important gains in propulsion efficiency have resulted from development of inlets, engines and exhaust nozzles which are matched over broad range of operating conditions; only steady-state matching of inlets, engines and exhaust nozzles is reviewed; significant step in providing high performance as well as high reliability and minimum complexity is use of secondary air pressure to control exit area of nozzle; combined analytical and experimental program demonstrated feasibility of this design feature.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Inlet duct-engine exhaust nozzle airflow matching for supersonic transport


    Additional title:

    Aeronautical J


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Inlet duct -- Engine airflow match and compatibility for supersonic aircraft

    Alford, J.S. / Davies, D.P. / Young, L.C. | Engineering Index Backfile | 1962


    Inlet Duct—Engine Airflow Match and Compatibility for Supersonic Aircraft

    Davies, D. P. / Alford, J. S. / Young, L. C. | SAE Technical Papers | 1962


    Engine/Inlet Matching for Supersonic Aircraft Design

    Dickman, Christopher A. / Takahashi, Timothy T. | AIAA | 2016