Abstract
This paper directs attention to the interrelationship between crack growth rate equations and the Normalized Crack Growth (NCG) curve concept used in the F-4 fighter damage tracking program. Crack growth rate equations, based on linear elastic fracture mechanics assumptions, provide the capability for predicting the influences of geometrical changes or of stress scaling. For the crack growth rate equations that describe the flight-by-flight generated data presented herein, generalized integral (or inverted) formulas are suggested that provide the rationale for developing NCG curves. Subject to the limitations described within the body of the paper, the NCG curve invariance assumption for tracking damage at different locations in an aircraft appears reasonable.
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