Estimation of the Maximum Angle of Sideslip for Determination of Vertical-Tail Loads in Rolling Maneuvers
Abstract
Recent experiences have indicated that angles of sideslip in rolling maneuvers may be critical in the design of vertical tails for current research airplanes having weight distributed mainly along the fuselage. Previous investigations have indicated the seriousness df the problem for the World War II type of airplane. Some preliminary calculations for airplanes of current design, particularly with weight distributed primarily along the fuselage, are made herein. The results of this study indicate that existing simplified expres- sions for calculating maximum sideslip angles to determine the vertical tail loads in rolling maneuvers are not generally applicable to airplanes of current design. A general solution of the three linearized lateral equations of motion, including product-of-inertia terms, will usually indicate with sufficient accuracy the sideslip angles expected in aileron rolls from trinmied flight. In rolling pull-outs, however, where the pitching velocity is rapid, consideration of cross-couple inertia terms in the equations of motion is necessary to obtain the sideslip angles accurately. The inclusion of the equation of the pitching motion seems desirable along with the lateral equations of motion in order to obtain the influence of pitching in the cross-couple inertia terms of the lateral equations. Pitching oscillations started during rolling maneuvers will be influenced by cross-couple inertia moments in pitch and may cause large variations in angle of attack which affect the horizontal-tail loads.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1952
- Accession Number
- ADA380568
Entities
People
- Ralph W. Stone Jr.
Organizations
- National Aeronautics and Space Administration