Effect of Reynolds Number on the Lateral-Stability Derivatives at Low Speed of Sweptback-and Delta-Wing-Fuselage Combinations Oscillating in Yaw

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 degrees to 32 degrees for the delta-wing models and from 0 degrees to 28 degrees for the sweptback-wing model. The Reynolds number range was from 0.7 x 10(exp 6) for the sweptback-wing model and from 0.9 x 10(exp 6) to 9 x 10(exp 6) for the delta-wing models. The tests were run for amplitudes of oscillation from 2 degrees to 10 degrees 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.