Pressure distributions measured in flight for ten in the range from M = 0.70 to 0.88 are compared with corresponding results from tunnel tests at a Reynolds number of 5.4 x 10 to the 6th power. In all these conditions the flow over the wing upper surface was supercritical. The scale effect is small but measurable, the shock wave tending to be slightly further aft in flight by up to about 0.05 c. Three other discrepancies between flight and tunnel results are: the suction level ahead of the shock over part of the span is somewhat lower in flight; there is a tendency for the shock-induced separation to extend to the trailing edge earlier in flight; and there are detailed differences in the flow through and behind the forward shock wave near the wing root. The first two of these effects are shown to be at least partly due to the presence on the aircraft wing surface of the external tubing used for measuring pressures. In general, apart from these particular differences, there is good agreement between the flight and tunnel pressure distributions. (Author)


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    Titel :

    A Comparison of Wing Pressure Distributions Measured in Flight and on a Wind Tunnel Model of the Super VC 10


    Beteiligte:
    G. C. Browne (Autor:in) / T. E. Bateman (Autor:in) / M. Pavitt (Autor:in) / A. B. Haines (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    71 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch