Application of Balancing Tabs to Ailerons
Abstract
Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effects of rolling velocity and of forces in tab link on aileron hinge moments have been included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1942
- Accession Number
- ADA800616
Entities
People
- Richard I. Sears
Organizations
- Langley Research Center