Wing Divergence of Trimmed Aircraft,
Abstract
By means of a simple theoretical model it is shown that wing divergence of a free aircraft can be defined using the static case of trimmed level flight. The same model also shows that the control angle per 'g' goes to zero at a speed near the fixed-root divergence speed and that there is a large change in the spanwise distribution of airload in going from a low speed to speeds above that of fixed-root divergence.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 03, 1986
- Accession Number
- ADP005858
Entities
People
- T. Niblett
Organizations
- Royal Aircraft Establishment