Advanced Metallic Structures: Air Superiority Fighter Wing Design for Improved Cost, Weight and Integrity. Volume 3. Stress, Fatigue and Fracture, Cost and Material Data

Abstract

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.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1973
Accession Number
AD0781808

Entities

People

  • D. F. Davis

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Air Force
  • Air Power
  • Air Superiority Fighters
  • Aircrafts
  • Assembly
  • Computer Programs
  • Engineers
  • Fabrication
  • Manufacturing
  • Manufacturing Engineering
  • Materials
  • Mechanical Working
  • Mechanics
  • Plastic Explosives
  • Spars
  • Test And Evaluation

Readers

  • Aerodynamics/Aeronautics.
  • Materials Science (Mechanical Engineering).
  • Software Engineering