The first missiles powered by ramjets were built essentially for the purposes of checking the flight performance of this type engine. They generally had just one air intake in the nose, which is the optimum position, aerodynamically speaking. Thanks to technological advances, the ramjet is now becoming an engine of great interest for military applications, which have imposed constraints on the shape and location of the air intakes on the missile. Knowing the flow around an ogival cylindrical body at incidence, it is possible to specify the position for the air intakes and to design their frontal section. For the coming generation of ramjet missiles, performance must be increased. At the present time, this means high maneuverability and long range. New design criteria were taken into account for this, not the least of which are the constraints to reduce the radar cross section. High maneuverability means the air intakes have to function well in the very distorted flow fields occurring at high angle of attack, where the integration of the air intakes with the body is essential. Long range flight can be achieved at high altitude and high Mach number. A compromise must be found between maximum performance in cruising flight and the requirements for climbing and final descent. For this, air intakes with movable parts are being studied, as well as noncircular cross-sections of fuselage giving optimum lift-to-dray ratios.


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    Titel :

    Supersonic Missile Air Intakes: Design and Development Criteria


    Beteiligte:
    G. Laruelle (Autor:in)

    Erscheinungsdatum :

    1988


    Format / Umfang :

    12 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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