NACA-TN-825

Abstract

INTRODUCTION <br>The rates of change of rolling-moment, yawing-moment, and lateral-force coefficients with yaw are important factors in the calculation of the--lateral stability of an airplane and, consequently, these parameters .have been the subject of extensive investigation by the ,NACA. The effects of such variables as tip shape, dihedral, taper, and sweep are reported in references 1 and 2. A theoretical determination of lateral-stability characteristics of' wings as affected by some of these factors is presented in reference 3. The effect of wing-fuselage interference on lateral-stability characteristics has been investigated for wings of various tapers and sweeps in such combinations with circular and elliptical fuselages as to form high wing, midwing, and low-wing monoplanes. These results are given id references 4 and 5. <br>The tests reported herein are a continuation of the investigation of wing-fuselage interference and were made with the circular fuselage and symmetrically tapered wing used in the tests described in reference 4. The chief variable was the longitudinal position of the wing on the fuselage. The wing was located one-half of the mean chord length' forward and rearward of the position used for the tests of reference 4. At each horizontal location the model "was tested as a high-wing, a midwing, and a low-wing monoplane. Data for the central position, taken from reference 4, are included for comparison.