A 2D Mach 2.2 internal compression inlet with 97 % total pressure recovery has been designed using viscid-inviscid computational tools. Losses are minimized by careful boundary layer management combined with shape design for weak shocks. The resulting inlet has reduced stability to unstart in the face of atmospheric and engine-born disturbances, necessitating the use of an active stabilization bleed system that recovers the disturbance-rejection capabilities required of modem inlets. Atmospheric disturbances that the inlet may encounter during supersonic flight are characterized. Two separate physical mechanisms for unstart are identified, and active control algorithms to prevent these forms of unstart are designed and demonstrated using 1D and 2D unsteady Euler simulations. The resulting actively stabilized inlet can withstand flight velocity, temperature, and angle of attack perturbations consistent with atmospheric flight.


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    Titel :

    Design of an actively stabilized near-isentropic supersonic inlet


    Weitere Titelangaben:

    Entwurf eines aktiv stabilisierten nahezu isentropen Überschalleinlaufs


    Beteiligte:
    Ahsun, U. (Autor:in) / Merchant, A. (Autor:in) / Paduano, J.D. (Autor:in) / Drela, M. (Autor:in)


    Erscheinungsdatum :

    2003


    Format / Umfang :

    11 Seiten, 14 Bilder, 1 Tabelle, 14 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Design of an Actively Stabilized, Near-Isentropic Supersonic Inlet

    Merchant, Ali / Ashun, Umair / Paduano, James et al. | AIAA | 2003



    Design of a Near-Isentropic Supersonic Inlet Using Active Control

    Umair Ahsun / Ali Merchant / James Paduano et al. | AIAA | 2005


    ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT

    CONNERS TIMOTHY R / HENNE PRESTON A / HOWE DONALD C | Europäisches Patentamt | 2016

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    ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT

    HENNE PRESTON A / CONNORS TIMOTHY R / HOWE DONALD C | Europäisches Patentamt | 2019

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