Accession Number:

ADA374002

Title:

Fatigue Crack Retardation Following a Single Overload

Descriptive Note:

Technical memo.

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1973-10-01

Pagination or Media Count:

16.0

Abstract:

This report proposes a modification to the Wheeler fatigue crack retardation model. The modified model is derived and then used to predict existing data for the number of delay cycles following a single overload in 2024-T3 Aluminum, 4340 Steel, and Ti-6Al-4V Titanium alloy. All predictions were within essentially a factor of two of the experimental data.

Subject Categories:

  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE