INVESTIGATION OF EFFECT OF SIDESLIP ON LATERAL STABILITY CHARACTERISTICS III - RECTANGULAR LOW WING ON CIRCULAR FUSELAGE WITH VARIATIONS IN VERTICAL-TAIL AREA AND FUSELAGE LENGTH WITH AND WITHOUT HORIZONTAL TAIL SURFACE

摘要

Power-off tests were made in the 6- by 6-foot test section of the Langley stability tunnel to determine the variation of the static lateral stability characteristics with vertical-tail area, fuselage length, and wing dihedral. Two NACA 23012 rectangular wings with rounded tips and dihedral angles of 0° and 5° were tested alone and in combination with three circular fuselages of different lengths. The wing-fuselage combinations were tested as low-wing monoplanes with and without a horizontal tail and with variations in vertical-tail area. The results are presented as curves showing the variation of the static-lateral-stability slopes with angle of attack, and the rolling-moment, yawing-moment, and lateral-force coefficients with angle of yaw.