A PRELIMINARY INVESTIGATION OF THE EFFECTS OF FREQUENCY AND AMPLITUDE ON THE ROLLING DERIVATIVES OF AN UNSWEPT-WING MODEL OSCILLATING IN ROLL

摘要

A model with separable wing and tail assembly was oscillated in roll through a range of frequencies and amplitudes of oscillation for an angle of attack of 6° and at one frequency and amplitude for two higher angles of attack in order to determine the effects of the unsteady motion on the rolling stability derivatives of the model and its 'components.nA variation of frequency or amplitude of oscillation in the range Covered at an angle of attack of 0° had no important effect on either the yawing moment due to rolling or the damping in roll for this unswept-wing airplane configuration. The only appreciable value of yawing moment due to rolling was shown by the fuselage-tall combination. This configuration experienced a reduction in magnitude of the derivative as either the frequency or the amplitude of the oscillation increased.