A law-scale -wind-tunnel Investigation .was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independ¬ently) on the rolling stability derivatives for a series of untapered wings. The rolling-flow equipment of the Langley stability tunnel was used for the tests.nThe results of the tests indicate that when the aspect ratio is held constant, an increase in the sweepback angle causes a significant reduction in the damping in roll at low lift coefficients for only the higher aspect ratios tested- This result is in agreement with available swept-wing theory which indicates no effect of sweep for aspect ratios near zero.
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