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An Investigation of the lateral control characteristics of a reflection-plane model equipped with a boundary layer control system
Abstract
An analysis has been made of the lateral control characteristics of a semi-span wind tunnel model equipped with a boundary layer control system. An estimate has been made as to the lateral control performance of a flight test airplane. The boundary layer control system consisted of blowing air over the aileron and blowing flap, and sucking air in over the suction flap.
I was found that the rolling performance would be greatly improved by boundary layer control. The estimated Maximum $\frac{pb}{2V}$ increased 129 percent when the boundary layer control system was operated; however, at the same time the adverse yaw was increased.
The use of boundary layer control increased the aileron hinge-moments but reduced materially the wheel forces. The landing speed of the flight test airplane was reduced about 10 percent because of the higher maximum lift coefficients obtained from boundary layer control.
Table of Contents
Summary -- Introduction -- Symbols -- Corrections -- Description of model and boundary layer control system -- Summary of preliminary testing -- Lateral control tests performed -- Application of wind-tunnel data to a flight test airplane -- Conclusions -- References
Description
Thesis (M.S.)-- University of Wichita, College of Business Administration and Industry, Dept. of Aeronautical Engineering