Download Free Summary And Analysis Of Horizontal Tail Contribution To Longitudinal Stability Of Swept Wing Airplanes At Low Speeds With List Of References Book in PDF and EPUB Free Download. You can read online Summary And Analysis Of Horizontal Tail Contribution To Longitudinal Stability Of Swept Wing Airplanes At Low Speeds With List Of References and write the review.

Available wind-tunnel data on the low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations incorporating unswept and sweptback wings are reviewed and analyzed. The characteristics of the flow behind wings and wing-body combinations are described and related to the downwash at specific tail locations for unseparated flow conditions. The effects of variations of tail position, variations of wing plan form and airfoil section, trailing-edge flaps, stall-control devices, and ground interference on the air-flow characteristics and tail contribution are analyzed and demonstrated. The more favorable tail arrangements are emphasized and their application to specific configurations is illustrated. The analysis of the factors affecting the horizontal-tail contribution is, for the most part, descriptive; however, an attempt has been made to summarize certain data by empirical correlation or theoretical means in a form useful for design.
Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longitudinal stability and the steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees and aspect ratios of 4 are presented.
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.