Damage Tolerance in Aircraft Structures - Stp 486

Front Cover
ASTM International, 1971 - Airframes - 254 pages
0 Reviews
 

What people are saying - Write a review

We haven't found any reviews in the usual places.

Contents

Effect of Thickness on the Fracture Toughness of 7075 Aluminum in the
16
The Influence of Curvature on Stress Intensity at the Tip of a Circumferential
39
Fatigue Crack Propagation in Stiffened Panelsc c POE JR
79
Material Toughness and Residual Strength of Damage Tolerant Aircraft
98
An Approach to Predicting the Growth to Failure of Fatigue Cracks Sub
122
Initiation and Growth of Fatigue Cracks in and Residual Strength of
144
Development of the Failsafe Design Features of the DC10T SWIFT
164
The Ballistic Damage Characteristics and Damage Tolerance of Wing Struc
215
The Significance of Fatigue Crack ClosureWOLF ELBER
230
Crack Propagation in Helicopter Rotor BladesM J RICH
243
Copyright

Common terms and phrases

Popular passages

Page 242 - Effect of Stress Ratio on Fatigue-Crack Growth in 7075-T6 and 2024-T3 Aluminum Alloy Specimens," NASA Technical Note D-5390, National Aeronautics and Space Administration, 1969.

Bibliographic information