Langley full-scale tunnel investigation of the factors affecting the directional stability and trim characteristics of a fighter-type airplane /

Tests were made in the Langley full-scale tunnel of the Grumman XF6f-4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wing-fuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive air-flow surveys of sidewash angle and dynamic-pressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to air evaluating the slipstream effects. The data obtained from the air-flow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability.Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia.Originally issued as NACA as Advance Confidential Report L5A30 (February 1945).NACA Wartime Report L-109.Includes bibliographical references.Tests were made in the Langley full-scale tunnel of the Grumman XF6f-4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wing-fuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive air-flow surveys of sidewash angle and dynamic-pressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to air evaluating the slipstream effects. The data obtained from the air-flow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability.Mode of access: Internet