Within slender body theory, vortex method is developed for study of aerodynamic interference between missile, in both captive and dropped positions, and carrying airplane; in crossflow plane, airplane fuselage is approximated by circle represented by doublet; airplane wing, pylons, and missile wing panels are represented by evenly distributed vortices; case of cruciform missile carried underneath vertical pylon or dropped therefrom on each side of airplane is considered; normal force, side force, and rolling moment on missile are computed; they agree with results obtained by electric analogy; ways of improving method in light of results obtained by latter, wind tunnel, and flight test of actual configurations are indicated. (12171)


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    Titel :

    Vortex method for study of airplane-missile aerodynamic interference


    Weitere Titelangaben:

    J Aircraft


    Beteiligte:
    Yang, H.T. (Autor:in)

    Erschienen in:

    Journal of Aircraft ; 5 , n 6 ; p 591-597


    Erscheinungsdatum :

    1968


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Aerodynamic study of airplane models

    Strub, F. | Engineering Index Backfile | 1946



    Computational Fluid Dynamics Modeling of Multibody Missile Aerodynamic Interference

    Sahu, J. / Edge, H. L. / Heavey, K. R. et al. | British Library Conference Proceedings | 1998


    Airplane propeller interference study

    Ober, S. | Engineering Index Backfile | 1926