NACA-TN-1404

Abstract

INTRODUCTION <br>One of the problems arising from the increased speed and wing loading of modern airplanes is the difficulty of obtaining high lifts for landing and take-off without impairing lateral control. If conventional aileron arrangements are used to satisfy the lateral-control requirements, the flap span is necessarily limited and the problem of obtaining the lift required for take-off or landing becomes quite important. When full-span flaps are used to obtain the desired lift coefficient for the airplane, the designer is faced with the problem of including and properly locating a lateral-control device on the airplane which will be effective in all flight configurations and have characteristics that will not be deleterious or objectionable. <br>The purpose of the present paper is to give the most pertinent part of the experimental data on the characteristics of lateral-control devices for use with full-span or almost full-span flaps. The data are, necessarily, greatly condensed and some data have been given in a form different from the original source. Additional information on any particular model may be obtained from the reference. (See reference 1 to 25 and table I.) <br>Data on conventional balanced ailerons have been reported previously in reference 26, and a collection of fairly large-chord control-surface data has been given in reference 27.