Advanced Metallic Structures: Air Superiority Fighter Wing Design for Improved Cost, Weight and Integrity. Volume 3. Stress, Fatigue and Fracture, Cost and Material Data
Final rept. 15 Jun 1972-15 Jun 1973
GENERAL DYNAMICS FORT WORTH TX CONVAIR AEROSPACE DIV
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This section presents the portion of results of the flight loads buildup and demonstration tests for the F-111 with 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. 13 and 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.
- Attack and Fighter Aircraft