He is known for his work in safety analysis of structures, and pioneered the finite element studies of planar cracks in three-dimensional finite bodies,[2] and the development of extensive stress intensity factor equations. These solutions are now considered to be classic contributions to Fracture Mechanics, and are used as benchmarks for new crack stress analysis methods. He developed the theory for predicting plasticity induced crack closure and software Fastran,[3] which is widely used in the aircraft industry.[4][5]
In 2001, Newman left NASA for a professorship at Mississippi State University, where he developed a Fatigue and Fracture Laboratory and a new ASTM fracture standard (E-2472).[6]
Many of the stress-intensity-factor solutions for crack configurations in the ASTM fatigue-crack growth and fracture standards were developed by Newman, along with stress-intensity-factor solutions and equations for three-dimensional crack configurations, such as surface cracks and corner cracks at holes. His life-prediction model and code FASTRAN is used to make life assessments of aircraft structures and is one of the life-prediction options in NASGRO. FASTRAN was successfully used to predict the onset of widespread fatigue damage in simulated aircraft fuselage components during the NASA/FAA aging aircraft studies in the 1990s.
He has pioneered the use of the critical crack-tip-opening-angle (CTOA) fracture criterion for aircraft structures, which was successfully used by Boeing-Long Beach to predict the residual strength of a damaged fuselage structure tested at Wright-Patterson Air Force Base within 5% of the failure pressure. Recently, he has promoted the use of the compression precracking test methods to generate fatigue-crack-growth threshold data without load-history effects.
Referencesedit
^Superstars of Modern Aeronautic, NASA (1964-2001)
^Newman, J.C., Jr. An Elastic-Plastic Finite Element Analysis of Crack Initiation, Stable Crack Growth, and Instability, ASTM STP 833, 93-117 (1984).
^Harter, James A. (1999). "Comparison of contemporary FCG life prediction tools". International Journal of Fatigue. 21, Supplement 1: S181–S185.
^J.C. Newman, Jr., A Crack-Closure Model for Predicting Fatigue-Crack Growth under Aircraft Spectrum Loading, NASA TM-81941, January 1981.
^Newman, Jr., J. C. (1992). FASTRAN II -- A fatigue crack growth structural analysis program, Technical Memorandum 104159. NASA.
james, newman, this, biography, living, person, needs, additional, citations, verification, please, help, adding, reliable, sources, contentious, material, about, living, persons, that, unsourced, poorly, sourced, must, removed, immediately, from, article, tal. This biography of a living person needs additional citations for verification Please help by adding reliable sources Contentious material about living persons that is unsourced or poorly sourced must be removed immediately from the article and its talk page especially if potentially libelous Find sources James C Newman news newspapers books scholar JSTOR April 2011 Learn how and when to remove this template message James C Newman is an American engineer and materials scientist known for his work on fracture and fatigue for aerospace vehicles NASA has listed him as a Superstar of Modern Aeronautics 1 He is known for his work in safety analysis of structures and pioneered the finite element studies of planar cracks in three dimensional finite bodies 2 and the development of extensive stress intensity factor equations These solutions are now considered to be classic contributions to Fracture Mechanics and are used as benchmarks for new crack stress analysis methods He developed the theory for predicting plasticity induced crack closure and software Fastran 3 which is widely used in the aircraft industry 4 5 In 2001 Newman left NASA for a professorship at Mississippi State University where he developed a Fatigue and Fracture Laboratory and a new ASTM fracture standard E 2472 6 Many of the stress intensity factor solutions for crack configurations in the ASTM fatigue crack growth and fracture standards were developed by Newman along with stress intensity factor solutions and equations for three dimensional crack configurations such as surface cracks and corner cracks at holes His life prediction model and code FASTRAN is used to make life assessments of aircraft structures and is one of the life prediction options in NASGRO FASTRAN was successfully used to predict the onset of widespread fatigue damage in simulated aircraft fuselage components during the NASA FAA aging aircraft studies in the 1990s He has pioneered the use of the critical crack tip opening angle CTOA fracture criterion for aircraft structures which was successfully used by Boeing Long Beach to predict the residual strength of a damaged fuselage structure tested at Wright Patterson Air Force Base within 5 of the failure pressure Recently he has promoted the use of the compression precracking test methods to generate fatigue crack growth threshold data without load history effects References edit Superstars of Modern Aeronautic NASA 1964 2001 Newman J C Jr An Elastic Plastic Finite Element Analysis of Crack Initiation Stable Crack Growth and Instability ASTM STP 833 93 117 1984 Harter James A 1999 Comparison of contemporary FCG life prediction tools International Journal of Fatigue 21 Supplement 1 S181 S185 J C Newman Jr A Crack Closure Model for Predicting Fatigue Crack Growth under Aircraft Spectrum Loading NASA TM 81941 January 1981 Newman Jr J C 1992 FASTRAN II A fatigue crack growth structural analysis program Technical Memorandum 104159 NASA ASTM fractureExternal links editOfficial Website Google Scholar Retrieved from https en wikipedia org w index php title James C Newman amp oldid 1193668017, wikipedia, wiki, book, books, library,
