NASA has successfully developed a new testbed configuration for experimentally evaluating embedded boundary layer ingesting aircraft propulsors in its 8'x6' Supersonic Wind Tunnel. This testbed meets the challenges of providing the necessary freestream flow Mach conditions and desired range and distribution of boundary layer thickness for embedded aircraft propulsion systems. The testbed consists of a 48ft long raised wind tunnel floor aircraft surface simulator and a boundary layer regulation system to produce propulsion-local aircraft aerodynamic flow fields. This durable special test equipment is designed to be installed in the wind tunnel's transonic test section and is capable of evaluating a wide range of subcritical and supercritical airframe-propulsion integration configurations for subsonic cruise aircraft. The wind tunnel and testbed are well suited for meeting the test requirements of these propulsors in the most cost efficient way and has been aerodynamically calibrated and proven through tests of a first-of-its-kind boundary layer ingesting propulsor.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Experimental Evaluation of BLI Propulsion: The Boundary Layer Ingesting Inlet/Distortion-Tolerant Fan Solution


    Beteiligte:

    Kongress:

    AIAA Propulsion and Energy Forum ; 2018 ; Cincinnati, OH, United States


    Erscheinungsdatum :

    2018-07-11


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch