This paper presents the results of ground-based and flight investigations that have been performed at NASA for the purpose of development of spoilers as trailing-vortex hazard alleviation devices. Based on the results obtained in these investigations, it was found that the induced rolling moment on a trailing model can be reduced by spoilers located near the mid-semispan of a vortex-generating wing. Substantial reductions in induced rolling moment occur when the spoiler vortex attenuator is located well forward on both unswept and swept wing models. In addition, it was found by ground-based model tests and verified by full-scale flight tests that the existing flight spoilers on the B-747 aircraft are effective as trailing vortex attenuators. Based on the results of wind-tunnel investigations of the DC-10-30 and L-1011 aircraft models, the existing flight spoilers on both the DC-10-30 and L-1011 aircraft may also be effective trailing vortex attenuators.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-tunnel and flight evaluation of spoilers as trailing-vortex hazard alleviation devices


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1977 ; Los Angeles, CA


    Publication date :

    1977-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :