Wall interference correction procedures seek to determine the required changes in certain flow or geometric parameters so that the difference between the flow properties at the model's surface in the tunnel and free air are minimized. A transonic and a linear correction procedure were developed for aircraft models. In addition to Mach number and angle of attack corrections, an estimate of the accuracy of the corrections is provided by the transonic correction procedure. Lift, pitching moment and pressure measurements near the tunnel walls are required. The efficiency and accuracy of the correction procedure are improved. Moreover, correction of both the wing and tail angles of attack is allowed. The procedure is valid for transonic as well as subcritical flows. However, for subcritical flows further approximations and simplifying assumptions are made, leading to a very simple and efficient correction procedure.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Wind tunnel wall interference correction for aircraft models


    Beteiligte:
    Rizk, M. H. (Autor:in) / Smithmeyer, M. G. (Autor:in) / Murman, E. M. (Autor:in)


    Erscheinungsdatum :

    01.01.1984


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Wind tunnel wall interference corrections for aircraft models in thetransonic regime

    RIZK, M. H. / MURMAN, E. M. / MIT, Cambridge et al. | AIAA | 1984


    Wind Tunnel Wall Interference Assessment and Correction, 1983

    P. A. Newman / R. W. Barnwell | NTIS | 1984




    Wind-Tunnel Wall Interference

    Tidbury, G.H. | Emerald Group Publishing | 1945