An investigation has been made to determine the damping in yaw and static directional stability characteristics for a flat-fuselage model having its major cross-sectional axis either horizontal or vertical, for a flat-fuselage model having its major axis horizontal in combination with a 45 degree sweptback wing, and for a canard model having a triangular horizontal control surface and a 45 degree sweptback wing.

Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail.