METHOD FOR CALCULATING THE ROLLING AND YAWING MOMENTS DUEnTO ROLLING FOR UNSWEPT WINGS WITH OR WITHOUT FLAPS ORnAILERONS BY USE OF NONLINEAR SECTION LIFT DATA

摘要

The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and yaving-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods are based on lifting-line theory and allow the use of nonlinear section lift data. The method presented herein permits calculations to be made some¬what beyond maximum lift for wings having no twist or continuous twist and employing airfoil sections which do not display large discontinuities in the lift curves. Calculations can be made up to maximum lift for wings with discontinuous twist such as that produced by partial-span flaps or ailerons, or both. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved.