The results of some conceptual studies on the development and aerodynamic design of lifting configurations feasible for hypersonic vehicles powered by airbreathing engines are presented and discussed. The configurations, including the waveriders, with three-dimensional (3D), so-called convergent inlets, were considered. These inlets are designed so that the supersonic flow over them has the streamlines converging in space. Besides, they have a compact throat cross-section shape close to a circle. The latter property facilitates the engine heat protection as against the conventional 2D (flat) inlets or axisymmetric inlets with the centerbody having the slotted throats. The research included, firstly, a class of convergent inlets and lifting configurations designed by combining the regions of supersonic inviscid uniform flows formed over swept wedges and V-shaped bodies. Another class of configurations is designed with the use of supersonic axisymmetric inviscid compression flows. Swept concave surfaces contoured to form 3D supersonic convergent compression flows were also studied. Under the said aerodynamic design a wide set of numerical methods from the simplest quadratic ones to the 2D and 3D ones was used. The results of parametric calculations of the configurations built are considered and, in particular, some questions concerning the integration of convergent inlets with the lifting surfaces are discussed.


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    Title :

    Aerodynamic design of integrated configurations including waveriders with convergent compression surfaces and inlets


    Additional title:

    Aerodynamische Auslegung von integrierten Konfigurationen, die Wellenreiter mit konvergenten Verdichtungsflächen und Einläufen enthalten


    Contributors:


    Publication date :

    1995


    Size :

    7 Seiten, 8 Bilder, 10 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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