AD-773 673

PLANE STRAIN FRACTURE TOUGHNESS (KIC) DATA HANDBOOKFOR METALS

ARMY MATERIALS AND MECHANICS RESEARCH CENTER

DECEMBER 1973

DISTRIBUTED BY.

1. S. KPMIUET t Uoo=

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PLANE STRAINl FRACTURE TOUGHNESS (KiC) DATA Final ReportHANDBOOK FOR METALS 1. 7ERFORMING ORO. REPORT NUMBER

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William T. Matthews f9. PERFOWAING ORSANIZATION NAME AND ADDRESS I*. PROGRAM ELEMENTrPROJECT, T?.SK

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10. SUPPLEMENTARY NOTES

It. KeY WORDS (Ceithwpe on et.erae side ii ncesas.w ind Identify by block number)

Fracture properties Tables (data)Thughness Experimental dataGriffith crack Static tests

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Block No. 20 ABSTRACT

-A compilation of plane strain KIC data is presented for metals manu-factured in the USA and Europe, including SO steels, 21 titanium alloys,38 alumiuum alloys, and one beryllium material. The data corresponds tostatic loading in nautral laboratory environment. The effect of tempera-tuie is included in the tables along with the direction of testing, theform and size of the material, its composition and heat treatment, andthe specimen type and size. (Author)

UNCLASSIFIED

%ECURi ry CLASSIFICATION 101 Y1hS PAGEMl•. DOM Fnt.md)

- - ., A----

TA8UF OF CO0%TENTrS

fitle Page

I.SrRODUCTION 1

DEFINITIN CF SYMBOLS AND UNITS

REFERLMCES

E BIBLIOGRAPHIIY

Kic DATA

A. Steel Tabl-.-

i. Low Alloy

AISi 43300I, EN30B3SN%016, L%40C 311-11AISI 4140 4AiSI 4540 5

MAC 7I'vZ4. Ni-Cr-!4o-i 8

ii. Nickel Steels

9.i--tzo-. 2C 99Ni.4Co- .% 109%i'4Co- .4-5C Hi10 Nickel 12

iii. Haraging Steel

12 Nickel 13IS Xi-200 Grade 1.11S Ni-250 Grade, DID$212, 6100, G110, M.-rval 18 is18 Ni-300 Gzade, G125 1618 Ni-350 Grade 17

: ,v. Stainless Steel

17-4 PII 1817-7 Pit 19Pl1lS.7"o 20PilIl83-1o. FVSZOR 21MU'43SS, AFC-77, AaC-20 22

v. Lcew Strength

AilS-C, ASTM A203 :

AISI 1045 24ASM; A216 25AMT! A'.•2, 26SAS"W! AS33 27,STMf A-42, ASM A543 28

vi. Intertwdiate Stt.•rth

AISI 1144, !fl 80 29ASMT A469, N-.o-V 30ASV4 A470, Cr-Mc-V 31XASr* A471, Ni-r-!P-- 32AS'11 AS•7-F, HY 130 33

a. Ttanium Alloys

i. a Alloy

SAI-2.S Sn 34

111 679, 1141 685, .Al-.Mo-IV, 6AI-2Sn-CZr-Z4o 3S

Uwll

B. Titanium ttlloYs (Cont.)

iii. u-8 Alloys

I4I SS0j, II 551, 6AW-3•1O 36

IA1 6 W 37

IA1-3No-IV, 7A1-2.,1o, 7AI-4'1o 38

6AI-4'V 39

6AI-6V-•Sn 40

6A1-6V-4Zr-4Mo, 6A!-2Sn-4Zr-6N'o, 6AI-2Sn-2Zr-3lo-2Cr 41

iv. 8 Alloys

13t'-I1Cr-3A. 8&4o-8V-2Fo-3A1. 11.5 Mo-62r-4.SSn, 3A1-8V-6Cr-4Zr 42

C. Aluminui Alloys

i. Copper Alloys

2(04, DTM 5020, 111) 66, BS 177, BS L93, GB-26S 43

2020 44

2021, 2219ZC-24. 2124, DTD S000, A-U4Gl 46

2613, RR 58, DTh 731, C01 003/41, A-U2QV 47

ii. Zn..Ig Alloys

7031, 7049, 7050 48

7007 49

7075, DID SOS0, 0TD 5074, BS L9S, AZ 74, 7175 sO

7178, DTD 363 51

iii. Zn-Mlg-Mn Alloys

"700!9. 7005 52

/079 53

DTD 5024, 1'W 50L. 54

7081), .- 75S 55

iv. Other Aiinum Alloys

6061 56

D. Beryllium

S-200 57

«1_

i.l-l

;¢"

INTRODUCTION

The plane strain fracture toughness values presented in this compilation are expressed in terms oflinear elastic fracture mechanics. These KIC values have been obtained by the ASTM' E399-72 "StandardMethod of Test for Plane Strain Fracture Toughness Testing of Metallic Materials" or a similar method.This data compilation includes materials manufactured in the USA and Europe. The following factors areinvolved in the selection and interpretation of the KIC values.

Testing Conditions

The material values shown correspond to quasi-static lo.ding of approximately one to three minutesduration. The environment is a neutral laboratory otivironment in which no aggressive chemicals orextreme of humidity are intentionally introdkuced.

Specimen Types

K values shown have been obtai-ied from AST? recommended bend and compact tensile specimens andfrom a variety of other specikens: four-point ben(, double cantilever beam, wedge opening loading, sideedge notched, center cracked specirens and a few double edge cracked and notched round specimens.Surface cracked specimen data is rot included in the appendix since, although this configuration isextremely important in applicatiens, criteria for validity of KIC measurements of surface crackedspecimens have not been establis'ied.

Criteria for Validity of Typicv.l KIC Values

The AST%1 E399-72 requirerents are taken as the general guide for validity. However, since completedetails of factors cited by ASli. are usually not available, personal judgment must be exercised. Forexample, although all data listed pertain to fatigue-cracked specimens, the range of imposed KI duringfatiguing is usually not repirted. In addition, the crack front curvature and the orientation of thecrack plane with respect to the loading axis are also unknown. Other typical unknowns are the criticalcrack length, the details of selection of the critical load value, the appearance of the fracture sur-faces, the details of fixture design to minimize friction and the linearity of the displacement gage.Therefore, it is often necessary to assume that in general the test measurements have been carried outaccording to good practice. In term of specific criteria for inclusion in this tabulation the ASlIlrequirement of thickness greater than 2.5 (KIC/eYS) 2 , was applied. Virtually .11 of the data satisfiedthis requirement. Although it would be destrable to require that crack length exceed 2.S (KIC/OyS) 2,this criterion wrs not rigidly imposed. Tite minimum reported crack length for data presented in thisappendix is 1.25 (KIC/oyS) 2 .

Accuracy of KIC Values

In general the KIC values shown are averages of several tests. The range of typical data may beinterpreted to be the average shown !10. In cases %here the range of toughness values was large,either the entire range is shown or the extremely high values were excluded before computing theaverage. It should be recognized that these accuracy limits rc'er only to the specific results obtainedand may not be appropriate in general for material of the s.,me nominal compositien, form, and sizewhich is processed and tested elsewhere.

Parameters Influencing KIC

Where available, the influence, whether significant or negligible, of material form and thickness,composition, heat treatment, testing t'.mperature and material anisotropy and yield strength upon KICis shown by the series of data entecred in the tables. In most cases uhere a particular heat treatmentprodces both the highest yield strength and toughness, data for other heat treatments are omitted. It

- - is important to note that for some materials, data from the cumbination of composition and processingwhich leads to the highest toughness is not included in this compilation. In those instances it is notpossible. to obtain valid ýIC measurements for the particular material thickness of interest. There areadd- ional'-,arameters Vaich may also influeice KIC values vhich are not shown in these tables since-the"are -r•tler infrequently reported. Thrse include melting practice, heat treating practice such asthe qize of quenching bath relative to the material size, and the amount of material straining during('orging.

DEHINITION OF SY'MBOLS AND UNITS

Ulits, Symbols and Nomenclature

Data is presented in the customary units tiw.ed in tize United States with accompanying InternationalSotem Units (SI) it, parentheses. The definitton of units and symbols for specimen orientation andtylu are Liven preceding the tabulations.

a) Composition and Heat Treatment CodesCode Form: Letter, NumberLetter - Identifies Compositionlumber - Identifies Heat Treatmenttetailed Jescriptions of composition and heat treaiment are at -.he bcttom of each table. The

compositional values are measured values in terms ef percentage by weight, except when designatedpps (parts per million).*en only specified composition is available, the nominal specifi.ed Ivel- are followed by theletter "W' and the maximum levels of other elements are followed by "'".

b) Orientation of SpecimensCode: First letter: Direction of Loading

W, L Second letter: Direction of Crack P'.opagationL: Ditection Parallel to Primary Grain Flow Direction of Plate, Forging or ExtrusionT: Direction Parallel te Largest Dimension in Plane Transverse to L DirectionS: Direction Parallel to Sualle., Dimension in Plate Tran,,verse to L DirectionST4: Prection 45S Between Directions of Largest and Smallest Dimension in Plane Transverse to L

� DirectionR: Radial DirectionC: Clrcumferential Dire tionIf a direction is ambiguous in terms )f two of the above definitions, thei both dirtctions are shown.

c) Specimen Identification

Bend: 3-point Bend SpecimenBend (4 pt): 4-point Bend SpecimenCT: ASIT Compact Tensile Specimen

SWIL: Similar to CT, but with different dimensiansCC: Remotely Loaded Flat Tensile Specimen with Center NotchDEC: Remotely Loaded Flat Tensile Specimen with Double Edge Cracks

SSEN: Remotely Loaded Flat Tensile Specimen with a Single Edge CrackNR: Round Tensile Specimen, Circumforentially NotchedDCB: Double C.ntilever Beam Specimen

d) Units

Temperature: F - Degrees FahrenheitK - Degrees Kelvin

Stress: KSI - Kips per Square Inchl'/m2 - Mega Newtons per Square Meter

Stress Intensity: KSI in- Kips per Square Inch Times Square Root Inches?IN m172 - Mega Newtons times (Meters)- 3/

Length: in, mm - Inches, Millimetersft, m - Feet, Meters

RFFERENCES

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4. Vishnevsky, C. and Steigerwald, E.A., Fracture Toughness Testinga_ onie Temperatr-es A5D45TP496,1971, pp. 3-26.

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2

____ - -R - -

17. Carter, C ,. nt. Trans., Vol 1, No. 6, June 1970, p 155?.

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3

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•A

~ - --- - - - ARE

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ASTM Standards, part 31.

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Review of Develonnents in Pl.ne Strain I'ractuie loughtiess restin 1 E ASl STP .163, 1970.

Plane Strain Crack Touliness r,,ting of Nigh Strength 'letallic Materials, ASP, :1P -110, 9),'.

Fracture roughness lestiny, and Its Ap~plieation-, ASIl Sil'l' 381, 19t,5.

Aerospace Structurtl M!etals HLandhook, AI'Il-TR-oS-I11, 1972 Publtcation.

"Planz! Strain Iractare Toughness Dtatat for Selected Metal.- ..nd \lloys," Battelle 'lemorial Institt., , D'IICN eport 5-28, June i:49

Leis, Ih., and Schiit:, h., "L'alua tion of Neu -\ircraft Structural 'laterials with the 'lethou of practurelccoanics" Air lorce S~steo- otnmand, foreign Technology, Ilt ision Tran.slation |T11-itF 23-1219-71, Poe.1971.

Steigcr'ald, L.A., "Plane strain I racture Toughness for Handbook Presentation," \I'll-TR-(,7- 1.7, Jul% 1907.

Goode, R.J., et a', t'tJ. rgigal t haracteristic.- of high Strength Structural 'Iaterials", 10th ProgressReport. Naval Research La:, Leport ,*4. lyr,ril 196.6.

6

"Puzak,-P.P., et al, "Metallurgical Chrracteristics of High Strength Structural Materials,, ilth ProgressReport, NRL Report 6513, Aug. 1966, AD646 52.

Goode, R.J., et al, "'letallurgical Characteristics of High Strength Structural Materials", 12th ProgressReport, NRL 6607. Sept. 1967.

Freed, C.N., Goode, R.J., and Judy, J.I., Eng Fracture Mich, Vol. 2, 1971, pp. 359-371.

Forney, J.•. "Fracture T.%ughness L-aluation of Titanium, Aluminum and Steel" Frankfert Arsenal ReportM66-20-1. March 1966. AD 632 926.

Witzell, W.E., "Fracture Data for Materials at Cryogenic Temperatures", AFT4L-lr-66-257, Nov. 1967.

Wit:ell, W.E., "Fracture Mechanics - Plane Strain Characteriatics of Severa; Aaterials at Low Temperatures",General -ynamics Report GDC-ERR-A.-1228, Dec. 1967, AD 854 611.

Cottrell, C.I..W., and Mn, "N.J., "Lineor Elastic Fracture Mechanics in the United Kingdon - Work of BISRAFracture Mechanics (hligh Strength Steel) Committee", B!SPA Report WG/E/160/69, %TIS PB 185 931.

Walker, E.F. and Hlay, H.J., "The Effect of Pro-Cracking Stress on the Plane Strain Fracture Toughness ofSSeveral !lartensitic Stees". BISRA Report MG/E/W,6/68.

Walker, E.F, and May, M.J., "Collaborative Fracture Toughness Programme Using Single Edge Notch TensionSpecimens", BISRA Report MG/E/401/6u.

Priest, A.H. and Mlay, .. J., "Fractu:'e Toughness of a Series of Experinental High Strength Steels", BISRAReport MG/E/404/66, NTIS, PB 185 433.

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Malters, J.N. and White, J.L., "Development of Fracture Toughness Properties of D6AC Steel for F-111Applications", AF4L-TR-70-310, Jan. 1971, AD 882 120L.

Hlarmsworth, C.L. and Iervay, R.R., "Fracture Toughness Evaluation of D6AC Steel in Support of the F-IllAircraft Recovery Program", Air Force Materials ULboratory TM-AFL/LAE 71-2, Dec. 1970.

V'ishnevsky, C. and Steigerwald, L.A., "Inflirmnce of Alloying Elements on the Toughness of Low AlloyMartens.aic Ifigh Strength Steels," Army Materials and Mechanics Research Center Report AM161I CR-60-09(F)Nov. 1968.

Ilauser, J.J. and Wells, -l.G.IH., "Inclusions in IHigh Strength Steels, Theii Dependence or ProcessingVariables and Their Effect on Engineering PropertieV', AMIL-TR-68-222, Aug. 1968.

Craik, R.L., et al, Metals Engineering Quarterly, Vol. 9, No. 3, August 1969.

Kalish, D. and Kulin, S.A., "Coupling of Ultrahigh Strength and Fracture Toughness in Steels by Means ofThermo-echanical Processes", ANL-.TR, 68-69.

CIE Ault, R.T., et al, "Development of an Improved Ultra-hligh Strength Steel for *Forged Aircraft Components",-AF M -1-71-27, Feb. 1971, AD 882 806,

Rolfo, S.T. and Gensamer, :1., "F-acture Toughness Requirements for Steels", U.S. Steel Project ARL-89.01?-O,

Coatract NOBS-94535, July 1968, AD 855 923.

Z= Carter, C.S., Met rrans., Vol. 2, No. 6, June 1971, p 1623.

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of a 35So Grade Uaragin; Steel", Boeing Commercial Airplane Group Report D6-22978, AD 692 169.

Simder, G.J. at al, Trans. Am. Soc. Metals, Vol. 60. 1967, p 418.

Tuffnell, G.W. and CArns, R.L.. Tra.saction quarterly, ASH, Vol. 61, No. 4, p 798.

Brand, R.A., and Rolfe, S.T., "Procedures for Dete-m';,ing KIC for 180/210 Yield Strength Steels", US.Steel Report 40.018-002(23), Dec. 1964.

webster,,D;, "iDevelopment of a High Streng.l. Stainless Steel with Improved Toughness and Ductility",Boeing Co. Report 06-25443, Scpti 1970, AD 712 724.

Judy, R.K. , et al, "A Characterization of the-Fracture Resistance of Thick Section Titanium Alloys" NRLReport -74Z7, July 1972,

WE Gooje, .R.J. et al, "Procedures for-Fracture-Toughnets Characterization and interpretations to Fa-lure-Safe Design Structural Titanium Alo-4, NRL Report 6779. Dec. 1966, also- .ld Res.-Council gull

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77

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Coyne, J.E., et al, M•tals Engineerinv Quarterly, Vol. i, No. 3, August 1968.

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Shannon, J.L. and Brom., W.F. J.-., Proc. ASfl4, Vol. 63, 1963, p 809.

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Lorenz, P.M.., "Effect of Pressurized Hydrogen Upon Inconel 718 and 2219 Aluminum", Boeing Co., AerospaceGroup Document D2-114417-1, Feb. 1969.

Zinkham, R.E. and Beker, C., Eng. Fracture %ech., Vol. 1, No. 3, April 1969.

Kaufman, J.G., et al, "Fracture Toughness, Fatigue and Corrosion Characteristics of 2020-T651,2024-T851, 2219-T851 and 7001-T75 Aluminum Alloys", AF ML-TR-66-291 AD 802 836.

Gerdeman, D.A., et al, "The Evaluation of Aerospace Materials, AFML-TR-68-53, March 1968.

Radon, J.C., Canadian Metallurgical Quarterly, Vol. 8, No. 4, 1970, p 297.

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Oct. 1967, N70-30070.

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Hiarrod, D.L., ,lengstenherg, T.F. and Manjoine, H.J., J of ,tls. N.Y., Vol. 4, No. 3, Sept. 1969, pp. 618-632.

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Fedde,- :, C.L., et al, "An Ixperimental and Theoretical Investigation of Plane Strezs Fracture of 2024-T7351-Aluminum Alloy Sheet and Plate", Battelle ,em. Inst. March 1970 AD 714 019.

Irwin, G.R., Journal of Basic Engineering, ASIE, June 1960, p 417.

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