Delta-canard shapes allow for maneuverable, supersonic combat aircraft. A configuration of medium aspect ratio was investigated to extend its maneuverability to very high angle of attack. Here, leading-edge vortex flows with intense interaction and breakdown effects dominate the flow. To appreciably enhance the maneuverability beyond limits, aerodynamic means had to be found. In-depth understanding of the interactions of the vortex systems was necessary to improve the aircraft capabilities. Unsteady Reynolds-averaged Navier-Stokes simulations simulations were performed via the unstructured DLR-Tau code. The aircraft was modeled without compromising geometrical details. It was found that asymmetric vortex breakdown features and unfavorable interactions at sideslips are the cause of the limited maneuverability. Means were deduced to control the vortex systems to mitigate or even avoid previous limits. This was done via a combination of theoretical thinking and computational fluid dynamics flow simulations. Aerodynamic means to control the lateral stability were investigated. Wind-tunnel tests secured this process. Small but effective fuselage strakes and leading-edge root extensions between the canard and the wing enhanced the lateral stability considerably. Much higher angle of attack can be reached for increased maneuverability. The design concept was confirmed through intense wind-tunnel campaigns and successfully flown in a test program covering the envelope.


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    Title :

    Enhanced Maneuverability of a Delta-Canard Combat Aircraft by Vortex Flow Control


    Contributors:

    Published in:

    Journal of Aircraft ; 55 , 3 ; 1090-1102


    Publication date :

    2018-05-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English