WL-TR-93-4076 THE MECHANICAL PROPERTY DATA BASE FROM … · improved mechanical properties, and/or...

AD-A269 694IIIINlUI Ill I lliiIll III

WL-TR-93-4076

THE MECHANICAL PROPERTY DATA BASE FROM ANAIR FORCFANDUSTRY COOPERATIVE TEST PROGRAM ON ADVANCEDALUMINUM ALLOYS (WELDALIIEWn 049 RX815 PLATE (2095-T"))

MARYANN PHILLIPS and STEVEN R. THOMPSONMaterials Engineering BranchSystems Support Division

May 1993

Interim Report for Period February 1991 - December 1992 M IGE

Approved for public release; distibution is unlimited.

Materials DirectorateWright LaboratoryAir Force Materiel CommandWright-Patterson Air Force Base, Ohio 45433-7734

93-21216

NOTICE

When Government drawings, specifications, or other data are used for any purposeother than in connection with a definitely Government-related procurement, the United StatesGovernment incurs no responsibility or any obligation whatsoever. The fact that thegovernment may have formulated or in any way supplied the said drawings, specifications, orother data, is not to be regarded by implication, or otherwise in any manner construed, aslicensing the holder, or any other person or corporation; or as conveying any rights orpermission to manufacture, use, or sell any patented invention that may in any way be relatedthereto.

This report is releasable to the National Technical Information Service (NTIS). AtNTIS, it will be available to the general public, including foreign nations.

This Technical report has been reviewed and is approved for publication.

MARY ANN PHILLIP, Projec-tngineer Y ENR. THOM1 N, Project EngineerEngineering.id Design Data Engineering and Design DataMaterials Engineering Branch Materials Engineering Branch

THE. RE T, ChiMaterials Engineering BranchSystems Support DivisionMaterials Directorate

THOMAS D. COOPER, CgfSystems Support Division fMaterials DirectorateWright Laboratory

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May 1993 Interim 2/91 to 12/92

4. TITLE AND SUBTITLE S. FUNDING NUMBERSThe Mechanical Property Data Base from an Air Force/ 62102FIndustry Cooperatie Test Program on Advanced Aluminum 2418Alloys (Weldalite 1 049 RX815 Plate (2095-T8)) 07

6. AUTHOR(S) 03

Mary Ann Phillips and Steven R. Thompson(513) 255-5063

7. PERFORMING ORGANIZATION NAME(S) AND ADORESS(ES) 8. PERFORMING ORGANIZATIONMaterials Directorate REPORT NUMBER

Wright LaboratoryAir Force Materiel Command WL-TR-93-4076Wright-Patterson Air Force Base OH 45433-7734

9. SPONSORINGIMONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORINGMaterials Directorate AGENCY REPORT NUMBER

Wright LaboratoryAir Force Materiel Command WL-TR-93-4076Wright-Patterson Air Force Base OH 45433-7734

"11. SUPPLEMENTARY NOTES

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Approved for Public Release; distribution unlimited

13. ABSTRACT (Maximum 200 words)

This report contains the development of mechanical property data base onaluminum-lithium alloy WeldaliteTM 049 0.5-inch plate. Basic mechanical propertydata consist of tension, compression, bearing, shear, and fracture- toughnessproperties. Fatigue data were developed for both smooth and notched specimens.Constant amplitude fatigue crack growth rate data and spectrum fatigue test datawere generated. Other tests performed on the material were ballistic, hardness,and conductivity.

14. SUBJECT T"OMS 15. NUMBER OF PAGESWeldaliteTm 049 8090 Tensile Bearing Spectrum 55Aluminum-Lithium AL9O5XL Crompression Fatigue Crack Growth 2095 16. PRICE CODE

2091 IN9O5XL Shear Fracture Toughness

17. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACTOF REPORT Of THIS PAGE OF ABSTRACT

Unclassified Unclassifed Unclassifitjd, UL

NSN 7540-01-280-5500 Standard Form 298 (Rev 2-89)Pretmr,bed by ANd Skti Z39-18

i 2 i i i i it i I

TABLE OF CONTENTS

SECTION PAGE

I INTRODUCrION I

II MATERIALS AND TESTS 3

In PRESENTATION 4

IV RESULTS AND DISCUSSION 5

V CONCLUSIONS 55

NTIS CRA&iOTIC TABUnannouncedJustification .......

By __..........Distr ibution /

Availability Codes

Avail andforDist Special

iii

LIST OF ILLUSTRATIONS

FIGUREPA

I1 Hardness Profile through 2095-T8 Plate 23

12 Ballistic Limit vs Armor Demand Data for 2095-T8 Plate 24

13 Fatigue Results for 2095-T8 0.5 Inch Plate (R = -1, Kt = 1.0 25and Kt = 3.0)

14 Fatigue Results for 2095-T8 0.5 Inch Plate (R = 0.1 28and Kt = 1.0)

I5 Fatigue Results for 2095-T8 0.5 Inch Plate (R = 0.1 30and Kt = 3)

16 Fatigue Crack Growth Data for 2095-T8 Plate (LT-LT 32Orientation, Specimen W45-1) Air Force

17 Fatigue Crack Growth Data for 2095-T8 Plate (LT-LT 34Orientation, Specimen W45-2) Air Force

18 Fatigue Crack Growth Data for 2095-T8 Plate (L-T and 36T-L Orientadons), Northrop

19 Fatigue Crack Growth Data for 2095-T8 Plate (L-T 37Orientation, KGRAD - 4.00 and 2.50), Northrop

110 Fatigue Crack Growth Data for 2095-T8 Plate (L-T 42Orientation, KGRAD 2.50), Northrop

Ill Fatigue Crack Growth Data for 2095-T8 Plate (T-L 45Orientation, KGRAD - 4.00 and 2.50), Northrop

112 Fatigue Crack Growth Data for 2095-T8 Plate (T-L 49Orientation, KGRAD 2.50), Northrop

113 T-38 LIF Spectrum Fatigue Crack Growth Data for 522095-T8 Plate (Max Stress = 38 ksi, Flaw = 0.01 inch),Northrop

114 T-38 LIF Spectrum Fatigue Crack Growth Data for 532095-T8 Plate (Max Stress = 38 ksi, Flaw = 0.05 inch),Northrop

115 T-38 LIF Spectrum Fatigue Crack Growth da/dFH vs 54a Data for 2095-T8 Plate, Northrop

iv

LIST OF TABLESTABLE PAGE

11 Tensile Results for 2095-T8 Plate, Longitudinal Orientation 6

12 Tensile Results for 2095-T8 Plate, Long Transverse Orientation 7

13 Tensile Results for 2095-T8 Plate, 45 Degree Orientation 8

14 Tensile Results for 2095-T8 Plate, Variable Temperatures 8

15 Tensile Results for 2095-T9 Plate, 1000 HR Exposure at 3500 F 9

16 Compression Results for 2095-T8 Plate, Longitudinal 10Orientation

17 Compression Results for 2095-T8 Plate, Long Transverse 11Orientation

18 Compression Results for 2095-T8 Plate, 45 Degree Orientation 12

19 Compression Ultimat,- Strength Results for 2095-T8 Plate 12

110 Pin Shear Results for 2095-T8 Plate, Longitudinal Orientation 13

IIl Rivit Shear Results for 2095-T8 Plate, Long Transverse 13Orientation

112 Torsional Shear Results for 2095-T8 Plate, Longitudinal and 14Long Transverse Orientation

113 Amsler Double Shear Results for 2095-T8 Plate, L-S and 15T-S Orientation

114 Bearing Results for 2095-T8 Plate, Longitudinal Orientation, 16e/D = 1.5

115 Bearing Results for 2095-T8 Plate, 45 Degree Orientation, 16e/D = 1.5

116 Bearing Results for 2095-T8 Plate, Long Transverse 17Orientation, e/D = 1.5

117 Bearing Results for 2095-T8 Plate, Longitudinal 18Orientation, e/D = 2.0

118 Bearing Results for 2095-T8 Plate, 45 Degree Orientation, 18e/D = 2.0

V

TABLE PAGE

119 Bearing Results for 2095-T8 Plate, Long Transverse 19Orientation, e/D = 2.0

120 Fracture Toughness Results for 2095-T8 Plate, L-T Orientation 20

121 Fracture Toughness Results for 2095-T8 Plate, T-L Orientation 21

122 Fracture Toughness Results for 2095-T8 Plate, 45 Degree 22Orientation

123 Hardness & Conductivity Results for 2095-T8 Plate 23

124 Fatigue Results with R = -1.0 and Kt = 1.0 for 2095-T8 Plate, 26Longitudinal Orientation

125 Fatigue Results with R = -1.0 and Kt = 3.0 for 2095-T8 Plate, 26Longitudinal Orientation

126 Fatigue Results with R = -1.0 and Kt = 3.0 for 2095-T8 Plate, 27Long Transverse Orientation

127 Fatigue Results with R = 0.1 and Kt = 1.0 for 2095-T8 Plate, 29Longitudinal Orientation

128 Fatigue Results with R = 0.1 and Kt = 3.0 for 2095-T8 Plate, 31Longitudinal Orientation

129 Fatigue Crack Growth Data Associated with Figure 16 33

130 Fatigue Crack Growth Data Associated with Figure 17 35

131 Fatigue Crack Growth Data Associated with Figure 19 38(Specimen F2GLIA)

132 Fatigue Crack Growth Data Associated with Figure 19 39(Specimen F2GLIB)

133 Fatigue Crack Growth Data Associated with Figure 110 43(Specimen F2GL2)

134 Fatigue Crack Growth Data Associated with Figure 111 46(Specimen F2GTlA)

135 Fatigue Crack Growth Data Associated with Figure 111 47(Specimen F2GTlB)

136 Fatigue Crack Growth Data Associated with Figure 112 50(Specimen F2GT2)

vi

PREFACE

This report was prepared by the Materials Engineering Branch (WIJMLSE), SystemsSupport Division, Materials Directorate, Wright Laboratory, Wright-Patterson Air Force Base,Ohio, under Project 2418, "Metallic Structural Materials," Task 241807, "Systems Support,"Work Unit 24180703, "Engineering and Design Data."

The authors would like to thank the participants U.S. Army Material TechnologyLaboratory MA, General Dynamics CA, McDonnell Douglas Missile Systems MD, NASALangley Research Center VA, Northrop CA, Sundstrand IL, and the U.S. Air Force MaterialsDirectorate for submitting their data.

vii

SECTION I

INTRODUCTION

High performance aerospace systems are dependent on materials that are lighter, haveimproved mechanical properties, and/or offer a cost savings. Aluminum alloys that met thesecriteria were the newly developed aluminum-lithium alloys and the second generation powdermetallurgy alloys.

In 1985, the Air Force along with the aerospace community found it important toinvestigate the potential of these promising aluminum alloys. A cooperative program wasformed by the Wright Laboratory Materials Directorate, Systems Support Division, and anumber of aerospace industries. The Air Force would obtain the test material from theproducers, compile the test data, and submit reports to the participants. The participants agreedto support the program by performing mechanical property tests which includes tension,compression, bearing, shear, fracture toughness, and fatigue related properties (S/N, da/dn).The Air Force elected to perform spectrum fatigue crack growth testing on most alloys. A listof participants is shown in the following table.

This interim report contains the aluminum-lithium alloy Weldaliteun 049 RX815 0.5-inch-thick plate produced by Reynolds Metals Company. The Weldalitetm 049 RX815 alloyhas been registered as 2095 with the Aluminum Association. Comparisons to other materials,and ranking of materials are generally avoided since each potential application may be based ondifferent evaluation criteria.

,,,,, i | |II

TABLE

Participants and Advan.ctd Aluminum Alloysin the Cooperative Test Program

ALUMINUM LITHIUM ALLOYS P/M ALUMINUM ALLOYS

PECHI EY AL InoA ALCOA REYNOLDS I(AUSER ACO

I¢1

PARTICIPANTS C ,f

Air Force WPAFB, OH x x x x A '

Amiy, MA I

AVCO, TN x

Boeing, WA X K

Ouglas Aircraft. CA x ixx x

General Dynamics, CA X K x x x x

General Dynamics, TX x x X x x x

Grum"ma Aerospace, NY x x x x X

Jet Propul•Son, CA x x

Lockheed. CA X

LO~cO,,G xx x A xLockheed. GA 11

LTV'TX x x x xx x x x x

Mariln Marietta. LA x x x x x x ix x x

McDonnell Douglas Astro, CA x

McDonnell Douglas Helicopler, AR x

McDonnel Douglas Missile Sys, MO x

McDonnell AIrcraft. MO x x X 9 A x x

NASA, VA x x x x

Nava Ak ODwmopment Center x x x

Northrop, CA x 4 4 A x lAX x x

Sikorsky, CTr x x ,

Sundstand, IL x

Wyman-Gordon

2

SECTION II

,MATERIALS AND TFSTS

The Weldaliteumn P-P eX815 (2095) 0.5-inch-thick plate was received the first quarterof 1991. The 2095 was received in the T8 condition. This alloy is considered to be a damagetolerant, medium strength aluminum-lithium alloy. A chemical analysis was performed on the2095 and the '.dioy chi mistry is shown below.

"fft We--tElement Weipght %

Copper 4.17 Iron 0.057Lithium 1.30 Nickel 0.0030Magnesium 0.339 Titanium 0.028Silicon 0.038 Zirconium 0.126Silver 0.334 Aluminum Balance

Basic mechanical properties (tension, compression, bearing, etc) were tested accordingto ASTM standards, unless otherwise specified. General Dynamics generated hardness andconductivity data. Constant amplitude fatigue crack growth tests were conducted according toASTM E647 standard. Northrop Corporation performed constant amplitude fatigue crackgrowth test using K controlled methods. A T-38 LIF (lead-in-fighter) spectrum test wasperformed by Northrop Corporation. The spectrum specimen was not precracked butcontained a countersunk hole to simulate a crack initiating from a fastener hole. The Armyevaluated the ballistic performance of the material. The Army and Northrop Corporation havecorrosion tests in process.

3

SECTION III

PRESENTATION

Each participant compiled a data package which contained the data they generated.Some of these data packages contain discussions, and in other cases, only the data wereprovided. The tensile, compression, bearing, shear, and fracture toughness data from eachpackage were put in tabular form. Fatigue, fatigue crack growth, spectrum fatigue crackgrowth, hardness, and conductivity data were placed in tabular and graphical form. Ballisticperformance data were put in text and graphical form.

4

SECTION IV

RESULTS AND DISCUSSION

The data generated by the participants on the 2095-T8 0.5 inch thick plate are shown inTables II thru 136 and Figures 11 thru 115.

5

TABLE II

TENSILE RESULTS AT t/2 LOCATION FOR REYNOLDS2095-T8 PLATE (0.5" X 24" X 48")

COMPANY TEST ORIENT- ULTIMATE YIELD ELONG RA ETEMP ATION STRENGTH STRENGTH (%) (%) (MSI)

(DEGREES F) (KSI) (KSI)

MCDONNELL RT LONG 89.7 85.7 12.0 23.7 10.9DOUGLAS, MO 88.4 84.3 12.0 19.7 10.8

86.8 81.1 12.0 26.4 11.4

SUNDSTRAND RT LONG 89.4 83.4 13.1 19.289.4 81.2 12.8 20.189.9 T53.7 13.0 19.3

ARMY-MTL RT LONG 88.6 81.9 12.9 10.888.2 81.3 11.7 10.987.7 80.4 12.9 10.4

GENERAL RT LONG 88.1 82.5 10.7 17.1 11.0DYNAMICS 89.2 84.9 11.0 21.3 11.0

89.1 84.6 10.0 17.6 11.2

NASA-LANGLEY RT LONG 88.0 81.2 12.3 11.284.9 75.6 9.6 11.385.0 77.2 9.6 11.3

NORTHROP RT LONG 89.7 83.6 13.9 11.588.1 80,6 13.0 11.189.0 81.8 13.6 11.0

AIR FORCE(-) RT LONG 89.4 83.1 7.4 27.0

MCDONNELL RT LONG 84.0 77.9 12.0DOUGLAS, CA 82.5 76.0 13.0

82.7 77.1 10.0

AVERAGE 87.6 81.3 11.7 21.1 11.1

STANDARD DEVIATION 2 2.9 1.6 3.5 0.3

(*): TEST SECTION DIAMETER = 0.16"

= m = .i i W | i N | 6

TABLE 12


COMPANY TEST ORIENT- ULTIMATE YIELD ELONG RA ETEMP ATION STRENGTH STRENGTH (%) M%) (MSI)


MCDONNELL RT L TRANS 87.0 80.8 11.0 23.8 11.1DOUGLAS, MO 87.0 81.1 11.0 26.8 10.8

86.8 80.8 11.0 28.4 10.9

SUNDSTRAND RT L TRANS 86.3 79.0 12.0 25.185.8 78.3 12.7 25.786.2 79.2 13.4 27.3

ARMY-MTL RT L TRANS 84.7 75.4 14.1 10.885.6 76.8 13.6 10.284.9 75.7 15.0 10.7

GENERAL RT L TRANS 84.0 75.6 11.4 21.9 11.0DYNAMICS 86.1 79.1 11.0 22.1 10.7

83.8 75.4 11.0 29.7 10.8

NASA-LANGLEY RT L TRANS 84.8 76.4 13.1 11.387.2 80.1 9.1 11.187.3 80.3 14.5 11.2

NORTHROP RT L TRANS 85.7 75.9 14.7 11.687.0 78.5 14.6 11.685.2 75.3 15.5 11.1

AIR FORCE(*) RT L TRANS 88.9 82.4 8.8 31.0

MCDONNELL RT L TRANS 81.2 71.7 14.5DOUGLAS, CA 80.5 71.0 14.5

81.8 73.0 14.0

AVERAGE 85.4 77.4 12.8 23.0 11.0

STANDARD DEVIATION 2.1 3.1 1.9 6.8 0.4

(*): TEST SECTION DIAMETER = 0.16"

l l I | | | | | 7

TABLE 13


COMPANY TEST ORIENT- ULTIMATE YIELD ELONG RA ETEMP ATION STRENGTH STRENGTH (%) (%) (MSI)


MCDONNELL RT 45 77.0 70.6 14.0 36.6 11.4DOUGLAS 77.2 70.1 16.0 39.1 10.9

76.3 69.2 17.0 39.3 10.8

AIR FORCE(*) RT 45 75.5 69.0 8.9 41.7 9.9

AVERAGE 76.5 69.7 14.0 39.2 10.8


4*): TEST SECTION DIAMETER - 0.16"

TABLE 14


COMPANY TEST ORIENT- ULTIMATE YIELD ELONG RA ETEMP ATION STRENGTH STRENGTH (%) M%) (MSI)


AIR FORCE -321(*) LONG 108.0 97.5 22.0 12.0L TRANS 104.0 93.8 9.6 26.0 11.7

-150 45 95.4 89.9 12.6 25.0 11.0

-100(*) LONG 92.3 86.2 8.8 27.0 11.045 78.7 71.5 11.4 21.6 11.5

L TRANS 91.9 85.0 8.0 26.0

-40 45 90.2 83.1 12.3 25.3 10.1

0 45 89.2 82.2 11.1 22.6 10.0

150 45 87.5 82.9 11.4 29.2 11.488.7 84.8 11.9 27.7 11.4

200 45 78.9 78.1 16.4 47.3 10.779.7 78.6 17.2 47.8 11.5

(w): TEST SECTION DIAMETER - 0.16"

• m m I l l i | m m 8

TABLE I5

TENSILE RESULTS AT t/2 LOCATION FOR REYNOLDS2095-TS PLATE (0.5" X 24" X 48")

(1000 HR EXPOSURE @ 350?)

COMPANY TEST ORIENT- ULTIMATE YIELD ELONG RA ETEMP ATION STRENGTH STRENGTH (M) (•) (MSI)


AIR FORCE RT 45 70.4 58.3 8.1 22.9 11.270.1 58.0 8.2 23.8 11.3

AVERAGE 70.3 58.1 8.2 23.3 11.2


9

TABLE 16

COMPRESSION RESULTS AT t/2 LOCATION FOR REYNOLDS2095-T8 PLATE (0.5- X 24" X 48")

COMPANY TEST ORIENTATION COMPRESSIVE COMPRESSIVETEMPERATURE YIELD STRENGTH MODULUS(DEGREES F) (KSI) (MSI)

MCDONNELL RT LONG 73.8 11.1DOUGLAS, MO 75.3 10.9

76.1 11.1

SUNDSTRAND RT LONG 73.1 12.073.3 11.873.8 11.7

GENERAL RT LONG 77.0 11.3DYNAMICS 79.0 11.6

80.0 11.4

NASA-LANGLEY RT LONG 62.3 11.4

NORTHROP RT LONG 70.9 12.272.2 12.176.7 11.9

MCDONNELL RT LONG 68.1 11.0DOUGLAS, CA 69.1 11.5

69.6 11.7

AVERAGE 73.1 11.6

STANDARD DEVIATION 4.5 0.4

10

TABLE 17

COMPRESSION RESULTS AT t/2 LOCATION FOR REYNOLDS2095-TS PLATE (0.5" X 24" X 48")

COMPANY TEST ORIENTATION COMPRESSIVE COMPRESSIVETEMPERATURE YIELD STRENGTH MODULUS(DEGREES F) (KSI) (MSI)

MCDONNELL RT L TRANS 79.5 11.8DOUGLAS, MO 78.5 11.8

79.1 11.6

SUNDSTRAND RT L TRANS 79.4 11.679.0 11.577.6 12.7

GENERAL RT L TRANS 79.2 11.4DYNAMICS 80.6 11.6

80.4 12.0

NASA-LANGLEY RT L TRANS 75.1 11.477.0 11.576.0 11.4

NORTHROP RT L TRANS 79.4 11.975.9 12.1

73.5 12.2

MCDONNELL RT L TRANS 72.9 14.0DOUGLAS, CA 72.3 13.5

73.2 13.8

AVERAGE 77.1 12.1


TABLE I8

COMPRESSION RESULTS AT t/2 LOCATION FOR REYNOLDS2095-TS PLATE (0.5" X 24" X 48")

COMPANY TEST ORIENTATION COMPRESSIVE COMPRESSIVETEMPERATURE YIELD STRENGTH MODULUS(DEGREES F) (KST) (MSI)

MCDONNELL RT 45 70.5 11.1DOUGLAS 70.3 11.0

72.2 10.9

AVERAGE 71.0 11.0


TABLE 19

COMPRESSION RESULTS AT t/2 LOCATION FOR REYNOLDS2095-TB PLATE (0.5" X 24" X 48")

COMPANY TEST ORIENTATION COMPRESSIVE COMPRESSIVETEMPERATURE ULT STRENGTH MODULUS(DEGREES F) (KSI) (MSI)

----- ---------------------------------------------------------------ARMY-MTL RT LONG 111.2

107.2110.7

AVERAGE 109.7

STANDARD DEVIATION 2.2

ARMY-MTL RT L TRANS 115.4119.0114.7

AVERAGE 116.4


12

TABLE 110

PIN SHEAR RESULTS FOR REYNOLDS2095-TS PLATE (0.5" X 24- X 48")

COMPANY ORIENTATION SHEARSTRENGTH

(KSI)

ARMY-NTL LONG 49.548.849.7

NORTHROP LONG 45.746.646.0

AVERAGE 47.7


TANLE Ill

RIVET SHEAR RESULTS FOR REYNOLDS2095-T8 PLATE (0.5" X 24" X 48")


(KSI)

ARMY-MTL L TRANS 49.048.547.7

AVERAGE 48.4


13

TABLE 112

TORSIONAL SHEAR RESULTS FOR REYNOLDS2095-TS PLATE (0.5- X 24" X 48")


(KSI)

SUNDSTRAND LONG 47.146.445.1

AVERAGE 46.2


SUNDSTRAND L TRANS 45.445.146.8

AVERAGE 45.8


14

TABLE 113

AMSLER DOUBLE SHEAR RESULTS FOR REYNOLDS2095-T8 PLATE (0.5" X 24" X 48")


(KSI)

NASA-LANGLEY L-S 44.446.347.7

AVERAGE 46.1STANDARD DEVIATION 1.7

NASA-LANGLEY T-S 47.545.645.0

AVERAGE 46.0STANDARD DEVIATION 1.3

15

TABLE 114

BEARING RESULTS FOR REYNOLDS2095-T8 PLATE (0.5" X 24" X 48")

COMPANY ORIENTATION O/D BEARING BEARINGULT. STR. YIELD STR.

(KsI) (Ksi)

MCDONNELL LONG 1.5 128.0 106.0DOUGLAS, MO 119.0 100.0

122.0 103.0

NASA-LANGLEY LONG 1.5 123.1 99.2119.4 98.4120.6 100.3

NORTHROP LONG 1.5 156.4 116.5154.3 114.3153.6 113.7

MCDONNELL LONG 1.5 120.2 102.1DOUGLAS, CA 121.1 101.9

121.1 101.5

AVERAGE 129.9 104.7


TABLE 115

BEARING RESULTS FOR REYNOLDS2095-TS PLATE (0.5" X 24" X 48")

COMPANY ORIENTATION e/D BEARING BEARINGULT. STR. YIELD STR.

(KSI) (KSI)----- --------------------------------------------------------------MCDONNELL 45 1.5 128.0 106.0DOUGLAS, MO 131.0 110.0

135.0 111.0

AVERAGE 131.3 109.0


i6

TABLE 116

BEARING RESULTS FOR REYNOLDS2095-T8 PLATE (0.5- X 24" X 48")


(KSI) (KSI)------ ------------------------------------------------------------

MCDONNELL L TRANS 1.5 125.0 106.0DOUGLAS, MO 129.0 105.0

131.0 107.0

NASA-LANGLEY L TRANS 1.5 122.2 98.4124.2 101.6124.7 99.4

NORTHROP L TRANS 1.5 158.7 121.1160.4 120.6160.2 128.5

MCDONNELL L TRANS 1.5 121.7 100.4DOUGLAS, CA 121.7 98.3

120.5 97.3

AVERAGE 133.3 107.0


17

TABLE I17

BEARING RESULTS FOR REYNOLDS2095-T8 PLATE (0.5" X 24" X 48")


(ESI) (KSI)

MCDONNELL LONG 2.0 164.0 128.0DOUGLAS, MO 159.0 131.0

158.0 130.0

NASA-LANGLEY LONG 2.0 114.5148.0 111.0146.7 112.3

NORTHROP LONG 2.0 183.1 120.6183.6 123.1182.5 122.7

MCDONNELL LONG 2.0 157.5 119.6DOUGLAS, CA 156.5 124.1

157.4 120.2

AVERARGE 163.3 121.4


TABLE 118

BEARING RESULTS FOR REYNOLDS2095-TB PLATE (0,5" X 24" X 48")


(KSI) (KSI)

MCDONNELL 45 2.0 172.0 141.0DOUGLAS, MO 166.0 136.0

169.0 138.0

AVERAGE 169.0 138.3


18

TABLE 119

BEARING RESULTS FOR REYNOLDS2095-T8 PLATE (0.5- X 24" X 48")


(KSI) (KSI)

MCDONNELL L TRANS 2.0 163.0 132.0DOUGLAS, MO 160.0 137.0

166.0 137.0

NASA-LANGLEY L TRANS 2.0 116.4154.5 116.6154.5 116.1

NORTHROP L TRANS 2.0 186.9 126.7188.5 131.2189.8 127.5

MCDONNELL L TRANS 2.0 155.4 122.1DOUGLAS, CA 158.9 124.6

156.8 122.9

AVERAGE 166.8 125.8


i9

TABLE 120

FRACTURE TOUGHNESS RESULTS FOR REYNOLDS2095-TS PLATE (0.5" X 24" X 48")

COMPANY ORIENTATION KIC Kq COMMENT(KSI inr0.5) (KSI inO0.5)

MCDONNELL L-T 26.3 (1)DOUGLAS 22.8 (2)

SUNDSTRAND L-T 30.230.0

ARMY-MTL L-T 26.837.3 (s),(3)33.336.4 (2),(3)33.7 (2)

GENERAL L-T 33.5 (2)DYNAMICS 30.7 (2)

30.1 (2)

NASA-LANGLEY L-T 27.025.3 (2)

NORTHROP L-T 37.7 (3)40.4 (3)43.3 (3)

AVERAGE 28.5 33.1


(1): INVALID DUE TO SURFACE CRACK LENGTH MEASUREMENTSEXCEEDED 10% OF AVERAGE CRACK LENGTH

(2): INVALID DUE TO Pmax/Pq > 1.10

(3): INVALID DUE TO a & B > 2.5(Kq/YS)**2

20

TABLE 121

FRACTURE TOUGHNESS RESULTS FOR REYNOLDS2095-T8 PLATE (0.5- X 24- X 48")

COMPANY ORIENTATION KIC Kq COMMENT(KSI in^0.5) (KSI in^0.5)

MCDONNELL T-L 25.8 (1)DOUGLAS 29.6

SUNDSTRAND T-L 29.129.0

ARMY-MTL T-L 40.2 (2),(3)35.6 (3)35.0 (2),(3)35.9 (2),(3)36.9 (2),(3)35.5 (3)

GENERAL T-L 31.4DYNAMICS 29.4 (2)

29.2 (2)

NASA-LANGLEY T-L 24.4

NORTHROP T-L 38.7 (3)38.3 (3)37.9 (3)

AVERAGE 28.7 34.9


(1): INVALID DUE TO SURFACE CRACK LENGTH MEASUREMENTSEXCEEDED 10% OF AVERAGE CRACK LENGTH

(2)t INVALID DUE TO Pmax/Pq > 1.10

(3): INVALID DUE TO a & B > 2.5(Xq/YS)**2

21

TABLE 122

FRACTURE TOUGHNESS RESULTS FOR REYNOLDS2095-TB PLATE (0.5- X 24- X 48-)

COMPANY ORIENTATION KIC Kq COMMENT(KSI InV0.5) (KSI in'0.5)

MCDONNELL 45 25.4 (1)DOUGLAS 23.6

(1)*: INVALID DUE TO SURFACE CRACK LENGTH MEASUREMENTSEXCEEDED 10% OF AVERAGE CRACK LENGTH

22

TABLE 123

Hardness & Conductivity Results for 2095-T80.5 Inch Plate. General Dynamics, CA

Alloy/Product Form Hardness Conductivity(RB Scale) (% IACS)

Weldalite 2095-T8 22 (al0.50 Inch Plate See Figure 17 (b)

(a) as received mill surface(b) machined surface

90

89 a. a

Hardness(Rb)

84 ,.,

83 . .

0.00 0.05 0.10 0.15 0.20 0.25 0.30 0.35 0.40 0.45 0.50

DPMh of PLUS On)

Figure 11. Hardness profile through 2095-T80.5 Inch Plate. General Dynamics, CA.

23

4000.

Proiectie dia. (in.)

3500. 7.62 mm AP 0.243

12.7 mm AP 0.428

3000, 12.7 mm FSP 0.495

20.0 mm FSP 0.784

~2500

o ............. ........... ....2000.

Eil1 soo. *.! ,""

IMFSP - AP1000. 0 8090 (Ex) U

0 Weldalite (P) 0

500 c 59P)[4

a. 5083 (P) [14] A

0 - ' ' I ', *" ' , ''... I ' I ' " I " !

0 10 20 30 40 50 60 70 80

Armor Demand (lb/ft 2 /in)

Both 8090 extrusions (Ex) and Weldalite plates (P) provided enhanced ballisticperformance over 2519 and 5083 Al alloys. The V30 ballistic limits against AP and FSPprojectiles at 0* obliquity are plotted versus Armor demand. The Armordemand is defined as the (density x thickness) I projectile diameter. The ballistic datafor different caliber projectiles superimpose on single curves for either AP or FSPprojectiles when plotted against armor demand. This technique allows designers toevaluate ballistic performance as a function of projectile type rather than for Individualmunitions. The AP and FSP projectile diameters are included as inserts in the plot.Ballistic data for 2519 and 5083 are included as the high and low ends of aluminum alloyscurrently being considered for structural armor applications The lower set of 8090and Weldslite data points for both AP and FSP projectiles represent 0.5 inch ballistictargets. The second series of data points for each projectile type represent stackedplates to provide 1.0 inch thickness. The ballistic limits of both AL-Li alloys areattributed to the witncss plate being perforated by spalling rather than by the projectileexiting the target.

Figure 12. Ballistic limit (V50 ) verses Armor Demand at 00 obliquity againstArmor Piercing (AP) and Fragment Simulating Projectiles (FSP). Army,

24

it ywolds2m9-Ta Pikj

60 .. ~,.~ Long, Kt=1

___ Long, Kf=3

1 i i H L Trans, Ktm3

0 40- 77--'TI

it i

A'

AO lit-'---

0-

IE.3 IE.4 1E+5 IE.6 IE.7 IE+8Cycles to Failure, NI

Figure 13. Fatigue Results for 2095-T8S 0.5 Inch Plate (R -1, Kt = 1.0 and Kt = 3.0)and 2095-T6 (R = -I and Kt = 3)

TABLE 124

FATIGUE RESULTS WITH R--1.0 AND Kt-1.0 FORREYNOLDS 2095-T8 PLATE (0.5" X 24" X 48")

COMPANY ORIENTATION STRESS CYCLES(KSI)

SUNDSTRAND LONG 65.0 7,SOO50.0 34,95040.0 73,82035.0 338,91030.0 1,240,95029.0 8,461,08028.0 3,489,83026.0 10,000,000 *

(*): RUN OUT

TABLE 125

FATIGUE RESULTS WITH Rm-1.0 AND Xt-3.0 FORREYNOLDS 2095-T8 PLATE (0.5" X 24" X 48")


SUNDSTRAND LONG 25.0 16,30020.0 29,46017.5 102,58015.0 133,92012.0 253,81011.0 11,796,000 *10.0 11,913,000 *9.0 10,000,000 *

(*)t RUN OUT

26

TABLE 126

FATIGUE RESULTS WITH R=-I.0 AND Kt=3.0 FORREYNOLDS 2095-T8 PLATE (0.5" X 24" X 48")


SUNDSTRAND L TRANS 30.0 8,62025.0 19,69020.0 90,00017.0 254,53015.0 1,024,21014.0 943,79012.0 2,110,28010.5 1,715,500

27

.. ...... .. ... .. . -- -- - - - - - --

60 - )

1 i:aAA.~w .

R--AI

20 ~ Army, Long* Northrop, Long

A McDonnell Douglas, Long

* McDonnell Dougla& L Trans 10 - T r TI I I I 1 11 11 1 1 1 il

IE+4 IE.5 IE+6 lEe.? IE+8Cycles to Failure, Nf

Figure 14. Fatigue Results for 2095-T8 0.5 Inch Plate (R =0. 1 and Kt 1.0)

28

TABLE 127

FATIGUE RESULTS WITH R=0.1 AND Ktal.0 FORREYNOLDS 2095-T8 PLATE (0.5" X 24" X 48")


ARMY-MTL LONG 60.0 54,22060.0 67,58055.0 191,52050.0 1,205,76046.0 290,04246.0 10,026,880 *

43.0 754,00040.0 10,010,000 *

NORTHROP LONG 70.0 39,42060.0 70,55055.0 87,94450.0 247,95045.0 623,76040.0 511,87040.0 3,000,00040.0 2,135,840

MCDONNELL LONG 55.0 106,010DOUGLAS, CA 55.0 120,950

50.0 149,62050.0 122,97045.0 398,91045.0 398,30040.0 1,000,00040.0 1,000,000

MCDONNELL L TRANS 60.0 34,170DOUGLAS, CA 55.0 53,870

55.0 69,80050.0 101,06050.0 80,47048.0 153,08048.0 229,57045.0 1,000,00045.0 1,000,000

(*): RUN-OUT

29

ROMO 2014 R&O-4~~

* General Dynamics. Long

I * Northrop, Long

40I- A McDonneillDouglas, Long. .. U McDonnell Douglas. L Tran

0 I- -1 ,1:1

1E+3 1E+4 1E+5 1E+6 1E+e7 1E.8Cycles to Failure, Nf

Figure 15. Fatigue Results for 2095-n8 0.5 Inch Plate (R = 0. and Kt = 3)

30

TABLE 128

FATIGUE RESULTS WITH R=0.1 AND Kt=3.0 FORREYNOLDS 2095-T8 PLATE (0.5" X 24" X 48")


GENERAL DYNAMICS LONG 25.0 38,20015.0 120,60012.5 155,50012.0 281,90011.5 417,10011.3 10,240,300 *11.0 10,000,000 *10.0 32,313,000 *

NORTHROP LONG 40.0 27,53035.0 84,82030.0 220,84025.0 20,83025.0 605,47025.0 1,535,48022.5 3,000,000 *

20.0 3,000,000 *

MCDONNELL LONG 25.0 28,540DOUGLAS, CA 25.0 ý5,320

20.0 78,41020.0 69,95015.0 1,000,000 *15.0 1,000,000 *10.0 1,000,000 *10.0 1,000,000 *

MCDONNELL L TRANS 40.0 6,331DOUGLAS, CA 25.0 28,860

25.0 32,94020.0 60,52020.0 91,03015.0 348,18015.0 271,49010.0 1,000,000 *

10.0 1,000,000 *

(*): RUN-OUT

31

10 -3-

Spec !nen: W45-1Te mp: 70OFOr ien tat ion : LT-LT 0

10"-4 _ Spec Lmen Type: CT

0

00

>0s 0

S-1. 0

-ol

C 0 0 = 0.1F0q. 20az

100

10 "-7 •

10DELTA K hks -ren £)

Figure 16. Fatigue Crack Growth Rate Data for 2095-T8 0.5 Inch Plate(LT-LT orientation, Specimen W45-1). Air Force.

32

' "' " ' ' • i I I I I I

!!ii!!!1!II i!!!.N NN . .. N... ... ...

QQO~~~~ 0 0 00 0 00 0 00 0 0

I !! 0 !!I!Q q q r 0 "'T!!-I -!!rf!! "'o

ltl

I!I ~I III 111 II1II IIItl/lllllllll l tlll/ll l t/

Cd~~~~~~~ -44 -1 -1 - - - - - - - - - -1 - -. -@9 - -49 -41 9 -d -d -' -' - - - -

@4 --- --- -- w 9 ~ 4 ' VI

8 ~1 O r l!3 .( @ Q '9 9 9 1 -9 9 0

- - - - - - - - -

•33

" 0i

-I NN O 00 ~ oo i.-O'y pO~i # oO io oo.

IS ~~ 3 333

,, i i i i I I I I I I

10 " -

F=

Specitmen: W445-2STemp: 70'F

Or Len tot ion : LT-LT10-4- SpecLmen Type: CT

0

0 -6 0

\le •oq 000

-0O10' 0

0

o-o= 0.100

a R= 0.1Freq.= 20 hz.

0

10 -I I I I I I I "

2 3 4 5 6 7 89 2

10

DELTA K (k s -L- .)

Figure 17. Fatigue Crack Growth Rate Data for 2095-T8 0.5 Inch Plate

(LT-LT orientation, Specimen W45-2). Air Force.

34

------ ----- -- -------I-I-- I ------ i -

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MI 11++i;iM110eill •~i 11 RH M! 248H 11H 1011111

is

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SI i 8 *a CA IZ 1 11 'Ias au M 1:

.080 00000P00000008 0000808 0000 0 00 o000800000 000.00000

35

10-3 FATIGUE CRACK GROWTH RATES

10-4

10 "

Z do/dN-CAK""V C- g.535E- 10

"10- o n 3.618

SPEC R or K KGRAD TEMPo F2CL1A 0.10 -4.00 80.0o m2us 0.10 z5o a0.0O F2GLZ 0.10 2.50 75.00 F2GT1A 0.10 -4.00 77.0

- M VZGTIa 0.10 2.50 77.0*F2GTM 0.10 2.50 77.0

10-8 AK (ksiV-in)

1 10 100

Figure 18. Fatigue Crack Growth Rate Data for 2095-T8 0.5 Inch Thick Plate

(L-T and T-L orientations). Northrop.

36

S10-3 FATIGUE CRACK GROWTH RATES

x

10-

10 0

Z do/dN-C&K"C- 9.078E- 10

-6 .10 n, 3.586

SPEC R or K KGRAD TEMP

0 I2GL1A 0.10 -4.00 80.0x FZGL1B 0.10 2.50 80.0

10-7

10-B AK (ksivr'n-)0I I I I I I I I I

10 100


(L-T orientation, KGRAD - 4.00 and 2.50). Northrop.

37

TABLE 131

Fatigue Crack Growth Data Associated with Figure 19 (Specimen F2GLIA)

AU-OrcolA6FrVD F'AT I UE CRACK<

cRaOWTH RArE ANALYS S

SPOECDI9W Id. F2GLIA Geometry CMT)

Contract # W902115N Orientation L-T

Materlal &Lal01lIoe Yield (ksi) 82.0

Te•perature (F) 80 Hodulus 11.1

Environment Lab. air

Specimen Dimensions (in)

Thickness 0.495 Notch depth 0.609

Width 2.997 Gage length 1.000

"Height 3.600 Alpha ratio i.250

Precreck Parameters

PIBx (lbs) 1471.0 Stress ratio (R) 0.10

Final a (in) 0.689 Kmax 6.00

Test Parameters

Initial a (in) 0.689 Initial K 8.00

K-gradient -4.00 Stress ratio (R) 0.10

K Coeff EvS/P Coeff Analysis Codes

0.886000 1.000980 KRP 2 0

4.640000 -4.669510

-13.320000 18.46010014.720000 -236.824997-5.600000 1214.880000

0.000000 -2143.570100

V'suel Observatfons

Ev8/P Crack (EVO/P) Crack (visual) Error CAF

19.54 0.689 0.656 -. 033 1.000

20.62 0.745 0.715 -. 031 1.000

21.33 U.766 0.728 -. 038 1.000

21.58 0.776 0.7S4 -. 023 1.000

21.67 0.780 0.757 -. 023 1.000

23.00 0.831 0.800 -. 031 1.000

23.65 0.855 0.818 -. 036 1.000

24.14 0.872 0.836 -. 036 1.000

25.06 0.904 0.870 -. 034 1.000

27.11 0.969 0.928 -. 041 1.000

29.75 1.045 1.017 -. 026 1.000

92.36 f.818 1.518 -. 000 1.000

EOo/P * N aa AN a/AmN AK

(1bs) (in) (XI) (In) (XI) (In/cyc) (kthiin)

19.64 0.6938 43981393 19.80 0.7011 11308 0.0130 13262 9.783E-07 6.89

1347 19.93 0.7067 17660 0.0118 14041 8.406E-07 6.70

1308 20.07 0.7129 25349 0.0125 17258 7.251E-07 6.55

1269 20.22 0.7193 34918 0.0126 20541 6.157E-07 6.38

1232 20.36 0.7255 45890 0.0120 22772 S.256E-07 6.23

1195 20.49 0.7312 57689 0.0117 26035 4.5051-07 6.08

1162 20.63 0.7373 7:925 0.0118 30699 3.849E-07 5.94

1128 20.77 0.7430 88368 0.0118 34418 3.416E-07 5.80

1095 20.91 0.7490 106343 0.0124 39201 3.158E-07 5.66

1063 21.07 0.7534 127S88 0.0123 44693 2.7611-07 5.53

1031 21.21 0.7614 151035 0.0120 48064 2.496E-07 5.39

1001 21.36 0.7674 175652 0.0121 51794 2.336E-07 5.27

974 21.51 0.7735 202829 0.0111 49535 2.2451-07 5.15

21.64 0.7785 22516721.82 0.7859 249807

688 21.97 0.7910 282411 0.0119 66418 1.796E-07 4.77

863 22.13 0.7978 316225 0.0121 69261 1.7454-07 4.66

838 22.28 0.8038 351672 0.0118 71831 1.6381-07 4.55

614 22.43 0.8096 368056 0.0116 73904 1.5741-07 4.45

791 22.59 0.S5ss 425576 0.0120 78049 1o.231-07 4.34

768 22.75 0.8216 466905 0.0122 85698 1.428K-07 4.24

22.91 0.6277 51127423.06 0.8341 53784323.23 0.8395 565306

38

TABLE 132

Fatigue Crack Growth Data Associated with Figure 19 (Specimen F2GL1B)

AUTOMATErD FPATIG'E CRACKGROaW.TH RATE ANALLYSIS

Specimen Id. FZGLUS Geometry C(T)Contract # WB021lSM Orientation L-TMaterial Welcial Ito Yield (ksf) S2.0TemPerature (f) 80 Modulus 11.1environment Lab. air

Specimen Dimensions (in)

Thickness 0.495 Notch depth 0.609Width 2.997 Gage length 1.000Height 3,600 Alpha ratio 1.250

Precrack Parameters

Pmx OIbs) 1471.0 Stress ratio (R) 0.10Final a (In) 0.689 Kmax 8.00

Test Parameters

Initial a (In) 0.855 Initial K 4.10K-gradient 2.50 Stress ratio (R) 0.10

K Coeff EvB/P Coeff Analysis Codes0.686000 1.000980 KRP 2 04.640000 -4.669510

-13.320000 18.46010014.720000 -236.824997-5.600000 1214.8800000.000000 -2143.570100

Visual Observations

EvB/P Crack (EvB/P) Crack (visual) Error CAF19.54 0.689 0.656 -. 033 1.00020.82 0.74S 0.715 -.031 1.00021.33 0.766 0.728 -. 038 1.00021.58 0.776 0.754 -. 023 1.00021.67 0.780 0.757 -. 023 1.00023.00 0.831 0.800 -. 031 1.00023.65 0.855 0.818 -. 036 1.000Z4.14 0.872 0.836 -. 036 1.00025.06 0.904 0.870 -. 034 1.00027.11 0.969 0.928 -.041 1.00029.75 1.045 1.017 -. 028 1.00092.36 1.818 1.818 -. 000 1000

Comments

Date of test: 08-12-1992

39

in. 0 4o %o~p Nm m~~ moa0 v~~. in %o N o, a0

W ZN9t :P 1:NP 4 i ;1-00d 4 i0 N0 0;. 0N 0; Oz0~ O 0 a.#E C; aC;C; 0' C

0=0~OO'

qNi-A mDN V N.p P NOO ONONNINN co,'MM V- p.~~-w,~~v~~~pN-q. P 0E N ~ ~ N~.C4~~.

V~W-NS ~ ~ NO ~flN~4 ~I~ !

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00,03000000000000000 00000000000

00~-'o 00- 0000O N8 N m

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s-p.N V~-sp v -~-psp NON;psp~--sp -A-~-~--p ~ ---

;; 6~~ q3~ ~ Pm V0?..V"tJ0

SPNPNS N400 WN 000 -- N M=VVN660p.!p.NWNSM - am.0- mpMq-

- "- p.0 nmv in I WSV VA %om inm" I M ;MPIMgNNNZN NNNN-

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40

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000N0000000000 M 0000000v

00000 a001 cc 00 000 N

N 100 ' -7-0W I W 7 1000000 N 'C 9 .99 N .n -0.100-0

t000000000M007-0100000 wW1wWIIW0WMWWWW

1-C' 0N-N- -0 -0N ' a n110'Mi O 0'O

w VV OW0 v v 1ý . rmr. -naNi I.. P ,r Om a-m 'CO 0NW7I- M0m0 -.9oo

00-N~M91001'Cni7--7 700000000000a000- c cc

M ! o 7- 0 ien I-N mm7- fn C4 0, vtoCiO o 1007010W

- 1 ''0C''CC' Wn C' 7--7--77--77- %77--7 0--700 000M0000 00 120

o N.9gf0000000NMWC7u000M 00700 cc a -0NM MOOG 00000000

0 ýco- NNM wNN N NN N NN N NN N WrNNN N N

vo e 0 , N, O M r "M V00" 00--N N ff OfID

.- 0MV0 P~ a 00000000 e00 w;00 0N00000

K~~~~~~!n' nnI,,IIlIIIICII

4100ni'CCnCn-


4/10./

0

10 - >%

Z do/dN-C&K"-V C- 1.977E-09

10 0 1n- 3.397

SPEC R or K KGRAD TEMP0 F2GL2 0.10 2.50 78.0

10e

AK (ksi-/il-)

10 - 1 1 ,1 1 -,L I I I I I IS1 t I I

10 100

Figure 110. Fatigue Crack Growth Rate Data for 2095-T8 0.5 Inch Thick Plate(L-T orientation, KGRAD 2.50). Northrop.

42

TABLE 133

Fatigue Crack Growth Data Associated with Figure 110 (Specimen F2GL2)

AUTOMATED FAT i GUE CRACKGROi•JTH RFATE ANALYSI S

Speclmen Id. F2GL2 Geometry C(T)

Contract # WB021I b. Orientation L-T

Material WELDALITE Yield (ksl) 101.0

Temperature (F) 78 modulus 10.6


Specimen Dimemiorms (in)



Height 3.600 Alpha ratio 1.250

Precrack Parameters

Pmax (Ibs) 911.0 Stress ratio (R) 0.10

Final a (In) 0.680 Kmax 4.91

Test Parameters


K-gradient 2.50 Stress ratio (RM 0.10

K Coeff EvB/P Coeff Analysis Codes0.88600n 1.00098o KRP 1 0

4.640000 -4.669510-13.320000 18.460'00

14.720000 -236.824997-5.600000 1214.880000

0.000000 -2143.570100

Visual Observations

Ev9/P Crack (EvB/P) Crack (visual) Error CAF

24.03 0.555 0.849 -. 006 0.985

25.57 0.909 0.910 0.002 0.986

27.48 0.970 0.972 0.002 0.9g8

30.72 1.063 !.069 0.007 0.991

32.46 1.108 1.110 0.002 0.993

34.22 1.150 1.150 -. 000 0.994

36.98 1.211 1.206 -. 006 0.996

Comments

Date of test, 01-28-1"92

43

C'JN N N fv t' NNNNMNM'I MM

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N4

S10-3 FATIGUE CRACK GROWTH RATES

x

xxxXX

io-

1-5

N._

Z do/dN-CAKn"- C- 1.297E-09

10- n- 3.512

SPEC R or K KGRAD TEMP0 F2GT1A 0.10 -4.00 77.0x F2GT1B 0.10 2.50 77.0

10-7

10_8 AK (ksivf)

I .I I I I t I . I I I I I I I II

1 10 100


(T-L orientation, KGRAD - 4.00 and 2.50). Northrop.

45

TABLE 134

Fatigue Crack Growth Data Associated with Figure I1I (Specimen F2GT IA)

AUTJOMATIG FAT I 0UM aRACKIGaROWTH RFATE ANALYSIS

Specimen Id. FZGTIA Geometry C(T)

Contract W WSO021SN Orientation T-L

Material WELDALITE Yield (kal) ,l.0

Temfporature (F) 77 POdulus 10.9


Specimen Diamions (In)


w'dth 2.997 Gage length 1.000


Precrack Parameters

Pmex (lbs) 1271.0 Stress ratio (R) 0.10

Final a (in) 0.901 Kmax 8.50

Test Parameters


K-gradfent -4.00 Stress rat'o (R) 0.10

K Coaff Eve/P Coeff Analysis Codes

0.886000 1.000980 KRP 2 0

4.640000 -4.669510

-13.320000 18.460100

14.720000 -236.824997

-5.600000 1214.880000

0.000000 -2143.570100

Visual Observations

EvB/P Crack (Evd/P) Crack (visual) Error CAF

24.97 0.900 0.872 -. 028 1.000

26.23 0.941 0.947 0.005 1.000

28.03 0.996 1.010 0.014 1.000

32.61 1.118 1.119 0.001 1.000

37.42 1.224 1.203 -. 021 1.000

40.54 .I285 1.261 -. 024 1.000

47.82 1.405 1.381 -. 024 1.000

50.85 1.447 1.426 -. 022 1.000

55.56 1.508 1.481 -. 027 1.000

58.77 1.545 1.525 -. 020 1.000

E 481P a N a AN 4/64N AK(Ib s) (0n) ( Kt) (in ) (X l) (In/ey c) (k al4 in)

25.44 0.9161 12656

1127 25.73 0.9256 21925 0.0183 18984 9.616E-07 6.93

1078 26.00 0.9343 31640 0.0174 2172Z 8.0181-07 6.68

1033 26.27 0.9430 43646 0.0174 28109 6.203E-07 6.45

989 26.55 0.9518 59749 0.0179 37173 4.808E-07 6.22

947 26.85 0.9609 80820 0.0183 45759 3.998E-07 6.01

906 27.15 0.9701 105508 0.0185 52122 3.552E-07 5.79

867 27.46 0.9794 132941 0.0183 57804 3.1641-07 5.58

829 27.76 0.9884 163312 0.0178 64272 2.772E-07 5.38

794 26.06 0.9972 197213 0.0178 71996 2.477E-07 5.19

28.37 1.0062 235308

46

TABLE 135

Fatigue Crack Growth Data Associated with Figure I II (Specimen F2GT1B)

AUTOMATE7D PAT I GUE CRACKGROWTH- RATE ANALYS I S

SpecImen Ia. F2GTIS Geometry C(T)Contract * WB0ZIISN Orientation T-L

Material WELDALITE Yield (koJ) 101.0Temyperature (F) 77 Mlodulus 10.9

EnvIronment Lab. air

Specimen Dimensions (In)

Thickness 0.486 Notch depth 0.614Width 2.997 Gage length 0.200Height 3.600 Alpha ratio 1.000

Pracrack Parameters

Pmax (lbs) 1271.0 Stress ratio (R) 0.10Final a (In) 0.901 Kmax 8.50

Test Parameters

Initial a (in) 1.064 Initial K 4.40K-gradient 2.50 Stress ratio (R) 0.10

K Coeff EvefP Coeff Analysis Codes0.886000 1.000980 KRP z 04.640000 -4.669510

-13.320000 18.46010014.720000 -236.824997

-5.600000 1214.8800000.000000 -2143.570100

Visual Observations

Ev3/P Crack (EvS/P) Crack (visual) Error CAF24.97 0.900 0.872 -. 028 1.000

26.23 0.941 0.947 0.005 1.000

28.03 0.996 1.010 0.014 1.00032.61 .1.168 1.119 0.001 1.00037.42 1.224 1.203 -. 021 1.00040.54 1.285 1.261 -. 024 1.000A7.82 1.405 1.381 -. 024 1.00050.85 1.447 1.426 -. 022 1.00055.56 1.508 1.481 -. 027 1.000

58.77 1.545 1.525 -. 020 m.000

Comments

Date of test: 01-14-1992

47

Va 0 'In00,0. 000 Vo 10,o 00 0 0 0 0 00

M enf"v vv n'O0.0P-43N - - - - NMP.

XX ~ .~m . % N m.in Nr 0'oi 0

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-~~~~~ 0W Ca'4 N0Mi.O W aMO i

a cc P- -M n an inf. i v0 i'-n CO

m In

c c 0 c c 0 0M OO i na N c 'oo aPu I f t iN 0 0 Q 010 0 1 1 1 1 1 1 1 i 1 1 1 1 1 1 1 i I t I

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42-C =61f 'O5 nmi0000M;v G o VNa oam; 0A N 0, 0 0 NoN 0 r.w : ma,20

mC mM M i0 W m -m a' 0 0 r 09 0 0w t OWUIfII 0 0N W iN 0 0F-0

O- -m ~ii- 0 0 %Wi~0 0'050N-'DW Mi¶i00'PP1O 0 cc a 0m 0

~- ONOWO~n~i OOrW - v%;fly wN m NWMOCON? MOOnN -0'.~N' DN-WaiM-0'5iiWWMPNi,.NNN----------

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0

00

10-,

10-5

C)

"Z do/dN•"CAKn"01 0 C- 2.813E-10

10-G ri- 4.108."0

SPEC R or K KCRAO TEMP

10 -GT2 0.10 2.5O 77.0

10 -'

1o_8 AK (kSiVII-)

10 100


(T-L orientation, KGRAD 2.50). Northrop.

49

TABLE 136

Fatigue Crack Growth Data Associated with Figure 112 (Specimen F2GT2)

AUTOMATE-D PAT GUE: CRACS<GROWTH RATE ANALYSIS

Spectimn Id. F2GT2 Geometry C(T)

o t WBZISN OrIentation T-LContract # W8021IT Yield (ksl) 101.0

Meteriat WEiLoAiITE j"OIu5u 20.8

Temperture (F) 77


Specimen Oimnatons 0in)




Precrack Parameters

A'x T Stress ratio (R) 0.10Pmx((be) 1166.0 KaC6.21

Final a (in) 0.665

Test parameters


K-gradient 2.50 Stress ratio (R) 0.10

K CoeFf EvB/P Coeff Analysis Codes

0.886000 1-000980 KAP 1 0

4.640000 -4.669510-13.3Z0000 18.460100

14.720000 -236.824997-5.600000 1214.880000

0.000000 -2143.570100

Visual Observations

EvB/P Crack (EvS/P) Crack (visual) Error CAF

21.66 .0.785 0.795 0.010 1.006

23.23 0.844 0.842 -.002 1.00523.23 1.003 0.990 -. 014 1.00134.29 1.154 1.151 -. 003 0.99836.97 1.213 1.219 0.005 0.997

46.28 1.377 1.379 0.002 0.993

Coo V ents

oats of tastt 02-12-1992

5o

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54,

SECTION V

CONCLUSIONS

Seven aerospace laboratories participated in generating data on the 2095-T8 0.5-inch-thick plate for the cooperative test program. These data combined with previous interim reportson the Air Force/Industry Cooperative Test Program on Advanced Aluminum Alloys providean extensive data base on aluminum-lithium alloys.

55

1U.S. fOVERNMENT PRINTING OFFICE 750-113

WL-TR-93-4076 THE MECHANICAL PROPERTY DATA BASE FROM … · improved mechanical properties, and/or...

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