References
W. Elber, in Damage Tolerance in Aircraft Structures, STP 486, American Society for Testing and Materials, Philadelphia (1971) 230–242.
J.C. Newman, Jr., Finite-Element Analysis of Fatigue Crack Propagation-Including the Effects of Crack closure. Ph.D. Thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA, May 1974.
J.C. Newman, Jr., “A Crack-Closure Model for Predicting Fatigue-Crack Growth under Aircraft Spectrum Loading”, NASA TM-81941, January 1981.
D.S. Dugdale, Journal of the Mechanics and Physics of Solids 8 (1960) 100–104.
J.C. NewmanJr., in Design of Fatigue and Fracture Resistant Structures, STP 761, American Society for Testing and Materials, Philadelphia (1982) 255–277.
C.M. Hudson, “Effect of Stress Ratio on Fatigue-Crack Growth in 7075-T6 and 2024-T3 Aluminum Alloy Specimens”, NASA TN D-5390, 1969.
Author information
Authors and Affiliations
Rights and permissions
About this article
Cite this article
Newman, J.C. A crack opening stress equation for fatigue crack growth. Int J Fract 24, R131–R135 (1984). https://doi.org/10.1007/BF00020751
Issue Date:
DOI: https://doi.org/10.1007/BF00020751