Experimental Determination of Dampling in Roll and Aileron Rolling Effectiveness of Three Wings Having 2, 42, and 62 deg Sweepback
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY
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An investigation on damping values in roll is presented. It is seen that these values decreased with increased sweepback. Method of obtaining approximate estimate of this reduction is shown. Damping in roll for all three wings decreased with increasing lift coefficient. Increasing amount of sweepback reduced the tendency toward instability in rolling as the maximum lift was approached and increased the aileron deflection required to produce a given value of the helix angle generated by the wing tip.
- Fluid Mechanics