Advanced Metallic Structures:Air Superiority Fighter Wing Design for Improved Cost,Weight and Integrity. Volume III. Stress,Fatigue and Fracture,Cost and Material Data.

摘要

This section presents the portion of results of the flight loads buildup and demonstration tests for the F-111with no external stores as applicable to the F-111F wing. The entire test program results are reported in Reference 1. These balanced symmetric flight tests were accomplished on F-111A No. 13and F-111A No. 75. These tests were accomplished to establish the maximum load levels encountered in flight. The ultimate objective of such testing is to show that the loads used for design and the loads applied in static test are adequate.