A Theoretical Analysis of the Effect of Aileron Inertia and Hinge Moment on the Maximum Rolling Acceleration of Airplanes in Abrupt Aileron Rolls
Abstract
Flight observations verify theory that increase of rolling acceleration is reduced by increase of hinge movement with air speed, when constant increment of torque is instantly applied to rigid control system having constant moment of inertia and hinge moment coefficient that varies directly with aileron deflection. Charts show ratio of maximum rolling acceleration theoretically attainable with instantaneous aileron deflection to that actually attainable with different combinations of pilot's effort, control inertia, and hinge moment coefficient.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1942
- Accession Number
- ADA800576
Entities
People
- F. J. Bailey Jr.
- William J. O'sullivan
Organizations
- National Advisory Committee for Aeronautics