Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds

Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tall locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data by empirical correlation or theoretical means in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 10(exp 6) and at Mach numbers less than 0.25

NACA Research Memorandums

Report presenting an investigation to determine the low-speed yaw characteristics of an airplane model with a 47.7 degree sweptback wing of aspect ratio 6 and to determine lateral stability contributions of various model components and associated mutual interference. The complete airplane model was directionally stable through the yaw-angle range for angles of attack up to 23 degrees

NACA Research Memorandums

Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided

NACA Technical Notes

Report presenting a study in the 19-foot pressure tunnel to determine the effects of fuselage afterbody shape, split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing swept back 42 degrees