Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers
Abstract
An analysis is presented of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight, as in rolls from turns or pull-outs, for example. The formulas derived show that the vertical-tail loads obtained in rolling pull-out maneuvers are directly proportional to the load factor, wing loading, and aileron effectiveness and are inversely proportional to directional stability. Sample calculations for an assumed fighter airplane are presented and discussed. It appears that critical tail loads may occur in rolling pull-out maneuvers, particularly on airplanes with good ailerons and low directional stability.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1944
- Accession Number
- ADA801519
Entities
Organizations
- National Aeronautics and Space Administration