EFFECT OF REYNOLDS NUMBER ONnTHE LATERAL-STABILITY DERIVATIVES AT LOW SPEED OFnSWEPTBACK- AND DELTA-WING-FUSELAGE COMBINATIONSnOSCILLATING IN YAW

摘要

An investigation has been made to determine the effect of Reynolds number on the lateral-stability derivatives at low speed of sweptback-and delta-wing—fuselage combinations. Results Were obtained from the models oscillating in yaw over an angle-of-attack range from 0° to 32° for the delta-wing models and from 0° to 28° for the sweptback-wing model. The Reynolds number range was from 0.7 x 106 to 7 x 106 for the sweptback-wing model and from 0.9 x 106 to 9 x 106 for the delta-wing models. The tests were run for amplitudes of oscillation from 2° to 10° and reduced-frequency parameters from 0.028 to 0.113. The results of this investigation are presented without discussion, but data figures are indexed in tabular form to facilitate their use.