A low-speed wind-tunnel investigation was made to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. The model was a flat plate with beveled leading and trailing edges, a maximum thickness ratio of 0.045, 60° sweepback at the leading edge, and an aspect ratio of 2.31.nThe results of the investigation indicated that a spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projections and were about the same magnitude for either the flap-retracted or the flap-deflected condition. Spoilers located just ahead of the double slotted flap were very powerful but had unsatisfactory variations of rolling-moment coefficient with spoiler projection and spoiler spans.
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