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.. 7-7* 7 7 7 7

,AFWAL-TR-85-41 14

ELEVATED TEMPERATURE PROPERTIES OF CAST ALUMINUMALLOYS A201-T7 AND A357-T6

Go.qdn J. D. Tirpak, First Lieutenant, USAF

Materials Integrity BranchSystems Support Division

S~~DTIC .::November 1985 TECTE qw"

.JAN30 1986

Final Report for Period 1982-December 1984 B -

Approved for public release; distribution unlimited.

L -. ' ' -

"� MATERIALS LABORATORYAIR FORCE WRIGHT AERONAUTICAL LABORATORIESAIR FORCE SYSTEMS COI4A.D

WRIGHTý-PATTERSON AIR FORCE PiAS!, 01110 45433-6533 Be tA albeCBestf Avilbl CP

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This technical report has been reviewed and Is approved for publication.

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6 Premium quality. Tvnsilie St ength. Fhtigue Crack Crowth,- A201-T7 . A'3r7-T6 , Frain L(r, rotip-lin ss

I S ABSTPACT Cuntiniue on revr:.s i I necesn-I and identifv Iý hI..l i ,m .b. # c.k

li Lu- i i *Ft igui' fracture ti'ughness. andd fat igut'1 C ravk growth p,.,r)\pert los of vast.1 ifluilinuv alloys A201 -IT7 -Ind A157-T6 were ev. ' i~ittvI :, 250OF and 40f I. .~h 'V e sli;trLrb-1tiI1 o(E A201-T7 decreased slightly at 2¶i0T ;,. dropped markedly at 4O0 F. 1lie

A2111-T7 elongatiion increased as temperattirL' Inc. tased. The tensleQ strength of A357-T6iascr' e ~ test temperatitire ine reaserl. A357-T6f duct I I ity increased then decreased as

tt.:'ipi ritt tire inervased. Valid fracture tougV..ioss values were (I ft icul t to (lhtaijý for!.,L al .~ys. A20,1ý1' had. an *uver~i~je F cf 22.3 k,;[ i n ait 25( r and. an average K of

25'(k-i n t *( V. F"or A357-*WY ~values werv 27.5~ ksI I n and 18-.l kst In at.5''I, I~rt-!y(I' t ivety . Cons tant I dad amp I ittude fat i.9tue st ren gth kledi' eased for hot h

* . . At l ow IK!;. f.it hi i~e orark g ,i (wtl) re, I i. tanck- ticcrva~ew as tv:,t t empi.'ra t ire

'I.P.HDU7ION A /AILAI3ILII f OF ABSTRlACT 21 A(331 FACT *iI.CURIrY CLASSIFICATION

I"e u5(ji~ I %L ',Akff - S PT flT C IJSFRS PilI-SSIiP

" ;. .. A- j kf(,')N, )ALUtF ýNDIViDJAL TEA. E. I WPINF NkUMIHLH1 22. ()F0 CL S MHOL

D tD FORM 1473.,83 APR t DI7 ION OF I IAN 13 1 OSo )I,'Ol I I.. 1; Nt

BEST AVAILABLE COPY

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PREFACE

This report vas prepared by the Materials Integrity Branch

(AFWAL/MLSA), Systems Support Division, Materials Laboratory, Air Force

Wright Aeronautical Laboratories, Wright Patterson Air Force Base, Ohio,

under Project'2418, "Aerospace Structural Materials," Task 241807,

"Systems Support," Work Unit 24180703, "Engineering and Design Data."

The work herein was performed between December 1982 and December

1984. The report was released in August 1985.

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TABLE OF CONTENTS

SECTION PACE

I BACKGROUND 1

II TEST PROGRAM AND PROCEDURES 2

A. Material 2

B. Specimen Geometry 2

C.. Test Procedures 8

III RESULTS AND DISCUSSION 9

A. Tensile Test Results

B. Fracture Toughness Test Results .9

C. Constant-Load-Amplitude Fatigue CrackGrovth Test Results 14

D. Constant-Load-Amplitude Fatigue TestResults 14

IV CONCLUSIONS 27

V REFERENCES 29

APPENDIX FATIGUE CRACK GROWTH RATE 31

I, "•• i :: :! 7 : , .. - ,"--

LIST OF FIGURES

FIGURE PACE

1. Step Plate Casting. 4

2. Tensile Test Specimen. 6

3. Fatigue Test Specimen. 6

4. Fracture Toughness and Fatigue Crack Growth Specimens. 7

5. A201-T7 Fatigue Data, R-0.1, (a) 2506F, (b) 400*F. 20

6. A357-T6 Fatigue Data, RmO.I,' (a) 250*F, (b) 400*F. 21

7. Combined Plots of Fatigue Data, R-O.1, (a) A201-T7,(b) A357-T6. 22

8. A201-T7 Fatigue Crack Growth Rate Data at 250*F. 23

9. A201-T7 Fatigue Crack Growth Rate Data at 400*F. 24

10. A357-T6 Fatigue Crack Growth Rate Data at 250*F. 25-

11.. A357-T6 Fatigue Crack Growth Rate Data at 400*F. 26

V1:L

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LIS•T OF TABL.ES

TLABLE PAGI:

Average Cbemistrie, of Step Plate&. 3

. leat TreCtrents.5

ill. Tens,,ile Test Results for A201-T7 at 150*V. 10L.

TV. Tensile Test Resulti; for A201-TI at 400e'F. 10 .

V. Tensile Test Results; for A357-T6 at 250*F. 11 '.

V1. Terrile Test Results for A?'ý7-76 at 400*F. 11 i

V. Fracture Tou~hnessq Test Fesults for A20IZýT7 at 2500F. 12

111T. FrActure Toughtiess Test Asults for A201-T7 at 400'F. 12 *

TX. fracture Toughness, Test Result.s frr A357-T6 it 250'3F. 13 "

X. Fracture lougbress Test Pesutlts for A357-T6 at W"~F. 13 e

XT.. Fatigu~e Data f~or A201-T7 -it '250°F, R-0.1. 16"-

YTI. Fatigue Data for A?O)-T7 at 4000Y, R-0.1. 17 "

YTTT. Fatigue Data foi A157-Tfi at 150"F, R-0.1. 18

0 0l

..TV. Fatngusile T for Aesu7tTh at 25(;F, at-0.1. 19

Vii

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0 0

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SECTION I

BACKGROUND

In the past, little emphauls has been placed on the durability and

damage tolerance of cast aluminum alloys A201-T7 and A357-T6. However,

several systems originated requests for such data demonstrate that not

Sonly are aluminum castings being used, but their use is also desired in

critical applications where damage tolerance design data is required.

Both the aerospace industry and the Air Force are aware of this

data need which must be filled before aerospace structural castings can

be used in fracture critical applications. Northrop Corporation, under

Air Force contract, developed much of the technology and data base to

get cast aluminum data into MIL-HBK-5. A part of this effort in-

volved obtaining castings from several sources and developing an alumi-

num'castings data base.

As part of this prngram, the Systems Support Division (AFWAL/MLSE)

3conducted fatigue crack growth testing. In addition, and in order to

generate the data requested by the System Program Offices, elevated .

temperature týsts were added to the program. These tests included

tensile, plane strain fracture toughness, const-ant-load-amplltude

fatigue crack growth, and constant-load-amplitude-fatlgue.

This report contains the the data generated for A?01-T7 and A357-T6 at

250*F and 40O°F.

j T

SECTION II

TEST PROGRAM AND PROCEDURES '..,

A. The materials evaluated in this program were the aluminum casting

alloys A201-T7 and A357-T6. A201 is an aluminum-copper-silver alloy and -

A357 is an aluminum-silicon-magnesium alloy (Table I). Both alloys have

respectable properties and are commonly used in aerospace applications.

For this program test plates were cast and heat treated to Mil-A-21180

requirements (Figure I and Table II).

The A201 plates were x-ray Grade "B" in the designated areas and

x-ray Grade "C" in the non-designated areas. Surface penetrant

inspection revealed no linear surface defects, and attached tensile '

coupons confirmed the heat treatment with tensile values of 60 ksi

ultimate tensile strength (UTS) and 55 ksi yield tensile strength (YTS).

Also, the minimum plate hardness was Rockwell B 70, and the minimum

plate conductivity was 31% IAC.

The A357 plates were also x-ray Grade "B" and "C" i the designated

and non-designated areas, respectively. The plate had no linear defects

and met the specified tensile requirements.

B. Test specimens were excised from the designated areas of the

castings and machined to the dimensions shown in Figures 2-4. The

thicknesses (B), for both the fracture toughness, and the fatigue crack

growth specimens, were machined as thick as possible while

maintaining the required surface finish. L"

"' "-C

C CO C C C C C C C �

CC COC QC� CC C C C C C C C

C CC

TABLE I

�Average Chemi�trIea of Step Pl�ites.

A?0l-T7 A357-T6

Cepper 4.7 0.01

Siticox. 0.08 6.87

Iron 0.04 0.07*� ?V. .*� .%

Pangan4�se 0.3 0.0!

* Zinc -- 0.01

Magnesium 0.3 0.53 ITitanium 0.2k 0.17 t ii

Bervl]itm -- 0.020*

SIlver 0.45 --

Aluminum Balance �alance

* Slightly lc'wer thz'r' VTL-2lIPOC chemical c�mpositir�n l1i�its.

If dC�

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TABLE II

Beat Treatments

SUPPLIER A201-T7 A.357-T6

A -Solutionize @ 9400F, I hr.-@ 960F?, 1 hr.n 980*, 12 hr..

-Water quench @ room temp.-Age @ 370*F, 5 hr..

3 -Solutionize @ 920*7, 2 hrs..@ 940o0 , 2 hro.

* 960*F, 2 hrs.@ 980*F, 18 hrs..

-Hater quench @ room temp.-Age @ 310*F 5 hrs..

C ----- Solutionize @ 1010*f, 12 hr..-Water quench @ ro temp.

-Age @ 330*P, 5 hrs.

D ------ Solutionize *1010FP, 16 hrs..-Water quench @ room temp.-Age @ 340'0 6 hrh.

• •ae qech@rom0ep

S-A~e@ 37"F, hrs

C 0 F

0~~ 00 0

2.625"(66.68)

.5- 1.625 0.375- 24 UNF(12.70) (41.28) CLASS 3A THOS,.125-- 1.250

L(318) (31.75)'-(Id

0.375 -_ _ _ _

(9.53) I0.125R RI- I (3.18)II0.250 DIA.

45S..,, --J•"',ooo •-- L'125 0.283,A

0.125 (6.35) 0IA..125 1 .1410.38) I1.000GL 8) (74)(3-18) (25.40) (31) 74'

4 TAPER 0.003 3 -(0.08)

TO CENTER

Figure 2: Tensile test specimen.

k* -. 1. 95 0.5-28 NEF

!::~~018 0.3 _=-

(49.5 7)

i: DIMENSION: INCHES

0mm

SFigure 3: Fatigue test specimen.

•ii••" , o ., 7... ....~.*Ir F .P - ~ s .~~w.

0 o~.c 8

C -DIAM.--

2HOLES..

D

B A Wv Wi D C

1'rac Lure 0.500 0.625 1.000. 1.250 0.600 0.25Toiu hness

(12.7) (15.9) (25.4) (31.8) (15.2) (6 .4)

li t i uv Crac k 0.50 1.50 2.000 2.500 1.200 0.50k.io) tit

(12.7) (38.1) (50.8) (63.5) (30.5) (12.7)

DIMENSIONS IN INCHES (mm)

ti -re 4 Frac tire toughness and fat Dgue crack growth

7

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C. The test procedures are briefly described as follovr:

Tensile tests were conducted ir acLordance with ASTK Te:.t Methods

A 557 and E 21. Tests were p.riuormed on a 10 kip Instron tensile test

machine with a Conrad-Missimer envtronmenta. chamber.

Plane stritn fracture toughness test specimens were precrAcked on a

?.? kip %ITS ,xial electrohydraullc fatigue machine and then pulled oil !'

--ip tensJle test machine with the specimen in a Conrad-Misblrer

ervironmental chamber. Tests were governed by ASTM! Test Metbod E 399.

Fatigue crack growth qrecimens wvre tested as outlined In ASTM Test

Metbed F 647. Tests were conducted on an MTS axial tatigue machine

and Conrpd-!Misstmer convection heating chamber.

Constant-load-amplitude fatigue tests were conducted as outlined In

"ASTM Test Method F 466. Tests vere conducted on a 2.: kip MTS axial

tatigiie machire with a split furnace surrounding the spe tmer (nd grips.

All tests were conducted in air while test temperatures were kept

' within ± 2.5" F.

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4 4

St l pSECTION III

•' RESULTS AND DISCUSSION

j A. Tensile test results for A20I-T7 were listed In Tables I Vl and IV.

A2VI-T7 room temperature tensile properties for the step plate castings

were 65.1 ksi UTS,60. 1 kal YTS, and 4.8% elongation. 5 At 250F, A20-T7

averaged 59.1 kst rTS, 54.6 kd i Ya S and 9.3% elongation. At yied the

A20I-T7 tensile properties were 47.2 ksi UTS, 44.2 kel YrS, and 1i.8%

- B- elongatuon.Tensile test results for A357-T6 were listed in Tables V and

tn VI. Roots temperature tensile propertdes for A357-T6 step plate castings

were of 48.8 ksi UTS, 41.1 ksi YTSh and 5.6 elongation.e At 250o f the

average tensile strength decreased to 43.3 ksi the average yield

strength dropped slightly to 39.3 ksi, and the average elongationincreased to 1O.1%. At 400"F, the average ultimate strength nearly

equaled the average yield strength at 35.8 and 35.3 ksi, respectively.j Also the elongation dropped off from 10.1%Z at 250"F to 8.0% at 400"F.

B. Fracture toughness test data were listed in Tables VTT-X. Of the

twenty tests conducted, only three produced valid K~c values. A201-T7

g had m wider range of KQ valueo than A357-T6; hoevere, three of the

A201-T7 values were valid. The average Kc value for A201-TT~at 250•F

• ~ ~~was 22.3 kst 'iT-- while the average KQvalue for A201-T7 at 400°F was 25.0

lksi/•i. At 2500F and 4O00F, the average KQ values for A357-T6 were 22.5

S~~and i8.1 ksi vTl'n, respectively. It was noted that the same problems

occurred in this test program as those which occurred in the CAST

. | Program. K~ values were not obtained because of thickness, crack

length, crack curvature, and/or P max/P requirements. 6

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C. Constant-load-amplitude fatigue data were listed in Tables XI-XIV ! .

and plotted in Figures 5-7. The A201-T7 curves were fairly smootht

(Figures 5 and 7a) and were in good agreement with data generated in

earlier investigations.7 There was a reduction in fatigue life fork% b%

A201-T7 at both 250" and 400*F. The most significant reduction occurred

5at lives greater than 10 cycles. The fatigue endurance limit was

approximately 14 ksi for A201-T7 at both temperatures.

The A357-T6 data exhibited more scatter than the A201-T7 data, but

for the most part the A357-T6 fatigue curves were fairly smooth (Figures

6-7a). At Ix l06 cycles there was little difference between the A357-T6

data at 250* and 400*F. The fatigue endurance limit was approximately

14 ksi. Although a room temperature data plot was constructed for

A357-T6, these data can not be compared because of the different

specimen configurations and R ratios. 8 In any event, A357-T6 has

greater fatigue strength at 250* than at 400*F at below approximately

5 64xlO cycles. At lives greater than IxlO cycles, the fatigue strength

at both temperatures are nearly equal.

D. The constant-load-amplitude fatigue crack growth rate data were

tabulated the Appendix and plotted in Figures 8-11. A201-T7 exhibited

slightly faster growth at 400* than at 250°F at the lower stress rIntensity ranges. At the higher levels of stress intensity range, the

crack growth rate data for both temperatures was near!y the same.

Compared to other data, A201-T7 at 2500 and 400°F bad lower Kc values9c

than room temperature data. During the testing of A201-T7, it was

noticed that there was good agreement between the automated crack length

measurements and the manual measurements at 250°F. This also occurred

at 400'F for specimen 2HC2, but most attempts at 400°F to measure cracks

14

0 0co

automatically failed so manual measurements were made instead.

The A357-T6 data also had faster crack growth rates at 400' than 250°F•..

at the lower ranges of stress intensity. Both the 250' and 400*F

fatigue crack growth rates were faster than at room temperature. 10

~i

A-o- .

4,i.2

Op . 4- d-

4-

0LF 40403

4.$

2LF1 48 1.30x10 5

2LF8 40 4.20xl10 4

5

2LF5O 25260I

2LF7l 45 1.30x104

2LF12 15 1.605x10

2LF13 25 6.60x10

2LF14* 143051

2L1456 8. 10100

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TABLE XII Fatigue Data for A201-T7 at 400F. RmO.1

� 4SPECIMEN MAXIMUM STRESS CYCLES � &

(kal)

�ii -

2HF1 *25 1.23x105

* 2liF2 18 4.37x105

2BF3 * 50 8.30x103S.

211F4 40 1.56x104

211F5 58 2.70,c103

2HF6 54 4.30x103

2HF7 20 1.72x105

214F8 45 1.23x10 4

2HF9 35 5.02x104

2HF1O 30 5.34x104

* 2HFIl** * 16 1.60x106

2HF12 --

2HF13* 15 1.00x107

62HF14 16 2.82x10

*Rtinoiit

**Failed In Lhreads

B.

0 �

'B �

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a o0 o' 00 %CTA0BLE ¾ 0 OQI 0atig0 Dat for A3 T at 200F R0.1

3LF3 00 0 C3x

3LF2 40 6.78xl103

3LF5 35 3.93x10 4

W L6 25 4.34x105

3L7 20 1.37xl10 6

3LF8* 15 1.01x107

WL9 17.5 9.44xl10 5

3LFIO 032 2.45xlO05

3LFIl 42 5.19xl10

3LF12 34 1.38x105

31113* 16 1.70xl107

3LF14 17 5.69xl05

* Run out

18

T ABLE XIV Fatigie. Data f oi A3I7-T& at 4O06F, R-n0. I

SPECIMIFN KAXI~hLM STRESS CYCLES

3HFI 171xl

20 9.52%105

3liF3 24 ) .OlxjO~

31FF4 35 5.44x104

3HF5 40 I.c1x10 4

3FF6 45 2.00x102

3HF7 43 2.00,c10

31!F8 41 6.00)X10 2

3HF9 41 5.80x103

3EFIO 16 9.53x106

3HP11 15 6.44xl10 5

3HF112 15 1.79x10'

.3HF'13 30 6.17xIC'4 .

3HF14 37 1.06x101

19

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14.3 _.__

is3 in in n111 in in

CYCLES

79.2

i RA201-T7, 40

LI

6"°.

a 7 S

CYCLES

R=0 (i 2017 (h) 400"1'5: A201 -T7 Foiligiiv Data , =(. , (a).

20

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V CYCLES

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21

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o Cc CCO# °"C o e oC00 o b&• o e Co C' c

9 0~t7 _20C

' / •c A201-T7f ZF IF

90. S . . 2IT•R.3 - - ." ....... .

0014140

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0

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8 m i£w c ikc ot Rt )I~ i Im v

23

ISO

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Tam- 4M Do. mfro. 5ism

cr.ic crowil PIv ); ,i

-- ý-

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*A257-TS/1.C1X A357-TO/3Lc x

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los

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ire - S

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20

SECTION IV

CONCLUSIONS

A. Tensile Properties

1. The ultimate tensile and yield strength of A201-T7 decreased

slightly at 250*F and decreased markedly at 400"F. The percent

elongation of A201-T7 increases as temperature increases.

2. The ultimate tensile and yield' strengths of A357-T6 decrease

vith increasing temperature. The ultimate strength of A357-T6 at 400"F

is slightly greater than the yield strength. The elongation of A357-T6

increases, then decreases, as temperature increases.

B. Fracture Toughness Properties

1. The average-- 1 for A201-T7 at 250*F is 22.3 ksili'n, while the .

average K. of A201-T7 at 400F* is 25.0 kslr~n.

2. The average K for A357-T6 is 27.5 kstdiW at 250OF and decreasesQ

to 18.1 ksi/in at 400*F.

C'. Constant-Load-Amplitude Fatigue Properties

1. The fatigue strength of A201-T7 decreases as temperature

increases from room temperatu.re to 250* to 400*F. The fatigue endurance

limif of A201-T7 at 250* and 400*F is approximately equal to 14 ksi.

2. The fatigue strength of A357-T6 decreases as temperature

increases form 250* to 400*F. The fatigue endurance limit is L

approximately 15 ksi at both temperatures.

27 7

÷./

0000 •o 0 . ' '" -00 o C o0o ~ Q0~. ' -

- 4

c C0 o 77c

°D. Fatigue Crack Growth Rate Properties

1. The fatigue crack growth rate of A201-T7 increases with

increasing temperature at low ranges of delta K.

2. The fatigue crack growth rate of A357-T6 increases with .

increasing temperature at low ranges of delta K.

28

or"

.oo .o o ° ° . .. .

SETION V

REFERENCES

1. K.J. Oswalt and C. Ford, "Manufacturing Methods for Process Fffectson Aluminum Casting Allowables," Contract F33615-79-C-5116, IR 268-9(1),_May 1981.

%. K.J. Oswalt, C. Ford, and Y. Lii, "Yanufacturing Methods for ProcessEffects on Aluminum Castlrj. Allowablen," Contract F33615-79-C-5116, IR268-9(11), May 1982.

3. J.D. Tirpak, "Constant-Load-Amplitude Fctigue Crack Growth Testingof Aluminum Casting Allovs A20J-T7 and A357-T6," AFWAL-TR-85-4096, July -1.1985.

4. K.J. Oswalt and Y. .Lii, "Manufacturing Methods for Process Effortson Aluminum Casting Allowables," Contract F33615-79-C-5116,AFWAL-TR-84-4117, March 19P5.

5. Oswalt, AFWAL-TR-84-4117, op.cit,.

6. E.K. Gunther, "Cast Aluminum Structures Technology (CAST), Strue-tural Test and Evaluation (Phase V), Part IT-Fatigue and FractureProperties of Cast Aluminum Bulkheads," Contract F33615-76-C-3111,AFWAL-TR-8n-3021, Part 11, April 1980.

7. O.L. Deel, P.E. Ruff, and H. MIndlin, "Engineering Pata on New"Aerospace Structural Materials," Contract F33615-73-C-5073,AFWAL-TR-75-97, June 1975. ,.

8. "Premium Castings-Product Manual," Aluminum Company of America,.1972.

9. Tirpak, op.cit.

10. Tirpak, op.cit.

29

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FArTCUF C�ACY GROWTH RAW DATA

,- *t .,

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4'

31

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1* JULL 1904

SPIJNEW I00. 2LCI AUIOMATIC

Pans e 775 LB Pair a 70 Ldt p * 0.101

560.494 In. W&Il.g? in.

PT CvCLIf A-cog A-qreq hUOtu oeI LJI7i In PC ISr3 ...1n/-..-.-...----..---.-------.--. ..--" ------..- ........................................... '-" 1

1 0.00) 0.5022 S9.36C 0.6073 119.490 0.622 , "4 175.350 0.638 0.630 0.999299 S.9,O 0.2991 °..5 219.800 0.653 0.652 0.999295 6.0 (A. 32216 273.140 0.648 0.670 0.999186 6.13 0.35667 312.310 0.664 0.683 0.997877 6. 6 0.4052* 350.040 0.699 0.699 0.999766 6.33 0.46939 • 304.920 0.714 0.716 0.990586 6.51 0."224 "

10 400A.1"9% 0.730 0.729 0.998781 6.64 0.569001 433.06 4.745 0.744 0.991920 6.77 6.6100

12 460.040 0

0.760 0.761 0.996632 6.91 0.700113 401.710 0.776 0.776 0.997739 7.0! 0.7478;4 503.54C 0.791 0.793 0.993495 7.10 0.0936is 55.650 0.806 0.004 0,993350 7-.34 0.990016 537.530 0.822 0.B27 0.993070 2.50 1.166117 543.610 0.837 0.834 0.993109 7..65 1.181910 57.-000 4.9s] 0.O52 0.993457 7.82 1.276319 $69.350 0.060 0.860 0.9927b3 1.9p 1.4231;0 562.02C0 0.803 0.805 0.997960 S.1I 1.611721 591.310 0.099 0.900 0.997926 3.33 1.945422 590.330 0.914 0.914 0.997902 A.S1 2.126523 605.320 0.929 0.930 0.990300 0.69 2.377224 610.420 0.945 0.942 0.997328 8.90 2.618225 61%.690 0.960 0.962 0.99587S 9.10 3.0987 L...26 623.290 0.975 0.976 0.996263 9.30 3.3793 ,27 626.440 0.99) 0.990 0.997490 9.!3 3.8218;,8 629.650 1.006 1.004 0.998219 9.76 4.136i29 , 634.150 1.021 1.024 0.99e240 9.99 4.449430 636.840 1.027 1. 635 0.996t97 10.25 4.8524 ' J-31 64C.270 1.052 1.052 0.997430 10.5o 5.4990 .op.. .32 643.310 1.067 1.070 0.996462 10.76 5.854733 645.280 1.083 1.001 0.996873 11.05 6.133034 647.490 1.090 1.096 0.995836 11.34 6.7893Is 650.46C 1..14 1.117 0.995628 11.66 7.545236 652.310 1.129 1.130 0.997922 11.97 6.063137 653 730 1.144 1.142 0.998209 12.30 ,..1. 238 .655•.670 1.16c 1.16C 0,998906 12.07 .6,39S39 6W !It 1.17S 1.17f 0.99614C 13.04 1I,.933140 656.6)0 1.190 1.190 0.996123 13.42 13.02244 660.q40 1.206 1.209 0.997572 13.14 15.055042 664. ;I0 1.221 1.221 0.99317o 14.27 15.628143 6c 46o .136

o,.

*.... ....-

44I. s'. ¶

32

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"2f JULY 1904

f1 CIPEN KC.. 2LC3 AUTCP.A'f K

Paa * 300 LOP p1rl I 00 L6F C. * 0.1O

&.0.492 ink. W-l.99b In9.

P? CYCLI A-ct A-%Ieq del tr8 da/cn

I CUUb1 An in MC I14I':. uin/cy

.* 1 0.CO1 0.4946.8 C 0.564

, '.3 93.2 0 0.580

"4 .26.6 C 0.59, 0.596 0.999286 5.79 0.4981• 152.7 0 0.611 0.61c 0.999)10 5.91 4.5416

6 181.4 .0 G.626 0.626 0.4999249 6.02 0.60,0"7 204.!,0 0.641 0.640 0.998578 6.14 0.6647

- 230.610 Q.657 0.658 0.%99444 6.21 4.7494

"9 249.94 0.672 0.672 0.99958 6.39 0.3044

* 10 26.$)0 (1.607 . 0.687 0.195L28 6.!1 0.797411 2S3.1,0 0.703 0.703 0.980439 6.65 0.9001

"12 30a.e)O 0.710 0.716 0.973364 .6.78 1.0231

1V 324.740 0.733 0.744 0.974707 6.91 .. 3?53

14 324.740 0.749 0.743 0.97#720 7.06 1.3826

i's 331.410 G.764 D.,62 0.971364 1.01.494C16 347.810, 0.779 0.768 0.977246 7.34 1.6676,17 354.R30 0.795 0.791 0.995954 1.49 1.62•0IS 367-.070 0.810 0.813 0.9960U4 7.44 1.80451 " 19 374.1'10 0.825 0.82g. 0.993P64 ?.80 2.0143"O 381.670 0.041 0.839 0.49617% 7.57 2.35611; 389.%o0 0.bS6 0.860 G.99C,136 8.13 2.7451:2 393.850 G.S72 0.871 0.997.45 1.21 2.9007

23 398.28, 0.887 0.8P5 0.99507 8.49 3.09602 4 4Cj.460 0.90: 0.904 0.999169 8.(7 3.;63425 407.590 0.918 0.916 0.997932 8.67 3.287;

26 412.94f. 0.933 0.933 0.997087 9.06 3.547827 417W.90 0.948 0.950 0.996998 9.26 4.0431

:8 421.15C o.964 0.964 0.998181 9.48 4.825429 424.30L 0.979 0.980 0.991F14 9.70 4.9(,68

30 427.06( 0.994 0.995 0.99?5T5 9.9: 5.2126

31 426.940 1.010 1.005 0.991808 1C.17 5.(1973? 433.19r 1.0:5 1.074 0.990352 10.41 6.4514?1 434.911. 1.040 1.041 r.4R644( 10.67 6.163;

34 431.00 1.C06 1.054 6.907065 10.95 6.2171

?5 43&.81G 1.071 1.067 0.9b9936 11.22 1.0077

36 442.2,P 1.086 1.089 0.980771 11.51 7..697

37 444.310 1.102 1.105 0.988550 11.83 10.60u3

38 44..-0 1.117 1.118 0.991367 12.14 11.3675

39 446.5 0 1.133 1.130 0.991990 1;.49 11.6114

40 447.f'C 1.14P 1.147 0.9979e2 12.84 12.336b

41 44 .. !0 1.163 1.16 0.994791 13.; 11.3359

42 45Si.tCý 1.179 1.17C 0.99225d 13.60 10.4097

43 452.5.0 1.194 1.198 Q.994146 14.c0 ' 12.1749

44 413.5!0 1.;Cq 1.209 0.994680 14.42 14.0806

45 454.44C 1.. "I46 4'5.570 1.-4C47 4 6.16 .I4u

3-'3

J oo 0 0o&

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60.492 in. W1.9908 in.

9P CYCLE A-tcor a4Iq*. deltt do/on# COUNI in Iii PC SIi41P ,uin/cy-- - - -- ---- --------- -------- ----------------------e'e~lt-• ----i • -- i e-------- /------------t--e--

'-' 0.001 0.S412 5S.0p.0 0.514

- 3 In0.Of'O 0.5864 140.0'0 0.619 0.615 0.992881 S.97 0.64065 170.0-0 0.633 0.634 0.994617 6.08 0.736)"6 200.( 0 0.654 0.656 0.995623 6.24 0.83697 22S.010 0.681 0.679 0.995856 6.46 0.8780a 250.0A0 0.704 0.703 0.998249 6.66 0.4363.S 270.010 4.724 0.723 0.998776 6.83 0.97c810 290.010 U.740 0.741 0.996570 6.97, 1.019711 310.C)o 0.761 0.761 0.V98202 1.17 1.158112 325.0)0* 0.778 0.778 0.999784 1.33 1.30331) 340.010 0.798 0.799 0.999010 1.52 1.5?14.4 i S.OW )I.623 0.823 0.999422 7.78 1.7463is 370.r)0 0.844 0.851 0.999262 8.06 1.9995lo 3s0.Lc) G.874 0.872 0.949141 6.34 2.159837 390.030 0.893 0.044 0.9984C5 &.56 2.40f8lp 395.030 Q.906 0.406 0.9976.42 6.72 2.11,8919 40.#30C Q.910 0.1#9 0.999731 6.87 2.7978o0 405'.(00 0.934 C.933 0.9%93SS 9.06 3.150c

21 410.00M 0.949 0.950 0.9993b8 9.28 3.435722 415.000 a.967 0.968 0.999476 9.53 3.7699.23 420.000 Q.989 0.987 0.99"461 9.85 4.1086

24 425.000 1.008 1.009 0.999540 10.14 4.418425 412.000 1.022 1.022 0.999443' 10.37 4,A30426 431.000 1.037 1.036 0.994C35 14.62 5.117027 434.000 1.051 1.051 0.998355 10.86 5.707120 437.000 1.067 1.069 0.998447 11.15 6.552429 439.000 1.084 1.082 0.999029 11.47 7.192730 443.000 1.112 1.114 0.99e206 12.04 8.412631 445.000 1.133 1.132 0.998261 12.49 9.668032 446.500 1.147 1.14S 0.997759 12.81 9.749633 444.000 1.158 1.159 0.997147 13.08 1.184134 449.500 1.172- 1.171 0.997005 13.42 9.77293S 453.000 1.135 1.86 0.998763 13.76 11.094636 4!2.500 1.202 1.204 0.996177 14.23 11.9M7337 453.100 1.210 1.216 0.991330 14.69 14.;12038 454.100 1. 232 1.232 0.987279 35.11 14.492839 4!S. 00 1.;41 1.246 0.982879 15.39 16.101840 456. 00 1.269 1.262 0.981539 16.34 1.113541 4MO. 00 1.283 1.292 0.968876 16.85 29.278042 4"8. be 1.304 1.30V 0A.72a5 17.66 35.482043 414. OC 1.31844 459. 00 1.352,45 45it. 0 ~ 1.363

34

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lost goo LOF LbV

.- I-1.441 In. v*|.44"e in.

' I• CYCL f A-€ r.r A.4i to

- -- -- - -- - -- - -

2 1.310 0.819

3 13.500 10.835S190.320 G.850 0.048 0.997903 9.08 2.3457

• S 40.460 G.%0.0911 0.4e961119 ak. (61 2.87115

," 0~ ~ 4S.360 01 0.912 (1. 9979132 &8 .5004.000 0.927 0.926 0.941 40 9,00 3.09334

. - • . , . 00" 1.20 -4. 1 "6

" 59 .90 0.973 0.972 Q.998909 9.63 4.7161

2 .2.1g0 0.819.. 15 9 1.85 4.05 1910 13.900 0.3

11 66.010 1.004 01:006 .9919947 10.10 6.9375

12 69.040 1.019 1 0.2 4.996146 10.24 S.1027

13 72.270 1.034 1.034 6.9980315 10.591 S.21917""7.4.060 0.927 1.067 0.997016 11.13 6.1316

81 0.2390 .7.99881 11.42 6.6794

"" 06 2.900 0.968 0.987 0.991)9770 11.7 7.6343

32 63.040 1.19 1.0C) 0b.998130 12.04 9.3159

14 S1.390 1.042 1.172 0.991634 13.41 13.3316

"15 90.920 1.180 10193 0.998313 13.87 16.0559

21 83.140 4.203 1.098 0.993740 116.73 7.343

22 83o.40 1.214 1.210 0.995l2 12.72 10.5949

23 94.350 1.23424 9S. 10 1.25025 95...0 1.265

35

0 0 0

27 J44% 39N4

lSI~I~M ML.21.C4 MPINAI

Poop - 000 Lb u r ar* u £.I I 1, b..NO

k*0.491 in. 16-..94. in.

NT VY& L I A-ur 9 .c c lt CAS/dIr0 t . i M I V.r

1 0.001 0.54112 3&.4flfl .S61

3 1 t00LOO 0.1.14 1503.001' 0.625 0.627 0.99.4657 6.4 3 0.8125'5 100.000 0.047 0.6149 O.9005'N 6.26 0.71106 210.000 0.674 0.f.72 0.94602? 6.42 0.66807 23S.000 •.695 0.095 4.99099S 1.59 4.97S6- 250.000 (1.708 0.710 0.998719 6.71 1.064/"9 26S.000 0.726 0.726 8.999SU4 .161 1.136110 260.000 U.744 0.744 0.949246 7.0? 1.211931 29S.000 0.764 0.763 0.99244 1.;1 1.306212 310.000 0.73 0.703 0.991438 7.19l 3.421513 325.000 0.602 0.804 0.998452. 7.56I 1.6187"14 335.000 0.620 0.420 0.999639 7.76 1.78001s 34S.000 0.039 0.631 0.999173 7.91 2.008416 3S5.000 0.360 0.860 0.999564 8.19 2.612017 36%.000 Q.612 0.663 0.099746 S.AS 2s4t;'3i6 375.000 0.910 0.910 0.999649 4.79 2.060719 382.000 0.930 0.10 0.99961.9 9.04 3..461820 38%.000 0.947 0.947 0.999591 9.27 3.540421 390.000 0.980 0.957 0.999673 9.41 3.773122 395.000 0.978 0.977 8.999297 9.70 4.2770"23 400.000 0.998 0.999 0.999661 10.01 4.I504"24 405.000 1.024 1.02S 0.999226 10.42 .5640"25 416.000 L.A0S 1.053 0.990S42 10.95 6.15342" 414.000 L.080 1.076 0.99S#34 11.42 I.1424"27 413.000 1.10. 1.106 0.996913 11.67 9.409426 421.000 1.132 1.13? 0.996204 121.40 10.11729 424.000 1.167 1.165 0.996479 10.33 12.S56130 426.000 1.104 1.103 0.99SS70 13.7 15.0250"31 42%.000 1.206 1.210 0.983824 14.37 20.6029"32 427.000 1.21633 425.000 1.. 4.34 427.500 1.516

___ ____ ____ ________ -. . 36

05 , oS 0. 0

] ~ 0 -c ~ ~

I0 0 o,'. o 0 - 5

C oo 0 0

17 JULV 1904

sPEC|IIfN No. 2NCd MANUAL

pvs - 7.00 LUP Poil * 70 Let P * 0.100

11.0.494 in. U-2.053 in.

A-Car A4 F! @I del tal 4/4W'O cOI .PC ,in C .. 61.ft ..

1 8.001 0.561a 35.000 0.5603' 65.000 8.596S 9S.000 8.611 0.612 4.999424 4.917 0.54S k91.000 ..621 0.62S 6.999770 1.09 0.6146

6 1SA.000 4.646 0.645 0.999717 5.20 0.6637

7 178.000 0.659 0.659 A."99596 0.26 8.6637

0 198.000 4.673 0.673 8.9"9245 S.37 6.0881

9 21G.000 0.687. 0.606 0.999227 1.47 0.7107

10 230.000 6.699 1 0.700 8.996304 S.S5 0.7714

31 250.000 2.716 \- 8.16 8.999172 5.67 0.0367

12 270.000 8.732 0.733 0.999220 1.79 0.9165

33 290.000 0.754 0.053 0.999512 1.95 0.99714 30.00 C.768 Ol. 760 0.999506 6.05 1.0511

15 320.000 0.184 0.784 4.994757 6.10 1.136116 332.000 0.18 0.801 0.999608 6.31 1.2366ý17 33S.000 0."k) 0.020 0.999623 6.46 1.3644

16 360.000 4.835 0.634 0.999541 6.60 1.44021s9 37.000 0.650 0.050 8.999365 6.73 1.495020 370.000 8.065 0.164 0.99606 6.66 1.639321 390.000 0.661 0.660 8.99745S %.01 1.7935

i 22 408.000 0.696 0.899 0.996446 %.15 2.0364

23 410.000 0.921 0.920 G.9"6354 1.39 3.3559

24 415.000 0.933 0.932 0.996110 1.52 2.4940

"25 420.000 0.947 0.946 8.996791 %.66 2.6921

• 26 421.000 0.951 0.960 0.997920 %.70 2.7143

27 430.000 0.973 0.973 0.997961 1.9S 2.0429

"28 435.000 0.990 0.966 6.99785% S .15 3.9979

29 440.000 1.001 1.003 0.997562 a.;$ 1.2393

30 44%.000 1.019 1.019 0.997960 1.50 3.5321

31 449.000 1.030 1.023 8.9924 4 1.64 4.3410

32 401.000 1.042 1.044 0.979399 1.0O 4.2)0233 456.000 1.054 1.050 6.962323 1.96 4.3767

34 451.000 3. '.080 1.072 0.964021 9.34 4.4287

35 463.000 1.093 1.097 0.981757 9.53 4.2475

36 466.000 1.107 1.109 0.977100 9.71 4.6426

4 37 469.000 1.122 1.121 1.999209 9.99 1.460136 471.000 1.132 1.133 0.999495 10.16 6.037539 473.000 1.146 146 0.999264 10.41 6.4326

40 47S.000 1.160 1.159 4.999429 10.66 6.9464

41 471.000 1.174 1.174 0.999723 10.93 %.3214

42 479.000 ; .169 0.998361 11.20 %.2500•'+ 43 401.t00 ., -5 1.204 0j99u569 11.56 1.1607

44 *o 0 1.216 0.994087 11.66 7.452145 44 4.000 •.0 1.232 0.992193 .12.13 1.2455

"""46 47.000 1.45 1.240 G.996939 12.47 9.229346 481.000 6 1.266 a.992675 13.02 12.4107

. 409.000 1.; 1.2a5 0.994129 13.56 1S.3625"-". 49 492.000 1.303 1.310 0.994626 14.02 19.0262

9 50 493.500 1.343 1.341 0.992661 IS.29 27.20M3

or 50 496.000 1.353 1.354 8.994640 11.64 33.210652 494.500 1.366 1.352 4.993582 '16.11 36.4962"53 495.000 1.392 1.390 0.996023 31.14 41.0503

"S4 490.300 1.406 1.405 0.973303 11.73 69.404755 495.600 1.421 1.427 Q.935623 16.41 114.2165

56 495.600 1.43557 496.000 1.474"5s 496.100 1.516

37

I "° 0 0o • 'Co0

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10 604.001 4.693 0.694 0.998620 4.93 0.374711 670.003 .0.725 0.723 0.999031 5.33 0.434312 920.0011 0.744 0.746 0.998627 S.;5 0.499913 960.000 0.764 0.767 0.990224 S.40 0.5484p14 965.00o) 0.779 0.760 0.996606 5.49 0.5071is 1010.000 01.797 0.795 0.994405 S.62 0.679717 1050.000 0.209 0.809 0.995031 5.70 0.6164617 1030.000 0.208 0.829 0.995307 5.70 0.7166is 1070.000 4.844 0.640 0.99S233 5.97 0.6843 .i9 1090.000 Q.656 0.060 0.995334 6.06 0.921420 1105.000 0.876 0.675 0.996683 6.23 0.800S21 1120.000 0.869 0.666 0.995470 6.34 0.8?4622? 113.000 0.901 0.900 0.994964 C.44 0.8318 423 1155.0CC 0.913 0.915 0.996902 4.54 0.822024 1170.000 FA. 9; 0.926 0.99342S 6.67 0.994925 1165.000 0.940 0.940 i. 995953 6.79 1.246C24 1200.000 0.957 0.96C 0.997561 4.94 1.S46327 121S.000 0.966 0.986 0.9$9401 7..25 2.135326 1225.000 1.000 1.009 0.996323 '1.49 2.731329 1230.000 1.0;1 1.023 0.997862 7.63 2.933430 1235.000 1.037 1.036 0.997573 2.62 3.232331 1240.000 1.C56 1.055 0.997306 8.07 3.5643X32 124S.000 1.071 1.074 0.997086 S.;4 3.910933 1241.000 1.065 1.005 0.996937 6.42 4.190034 1251.000 1.096 1.096 0.996262 6.60 4.264735 1254,.OOC 1.11? 1.112 0.999394 9 .60 4.500034 1251.000 1.127 1.126 0.999361 9.02 4.4S2437 1260.00C 1.136 1.139 0.999420 9.19 4.381036 1263.000 1.152 1.152 0.999080 9.42 4.349039 1266.000 1.165 1.164 0.999533 9.63 4.404840 12t9.000 1.177 1.176 0.999384 9.64 4.464341 1272.00C 1.192 1.191 0.997573 10.11 4.714342 127S.0100 1.;06 1.205 0.996113 10.37 5.252743 1:79.000 1.216 1.221 0.q99463 10.61 4.212144 1261.000 1-139 1.240 0.f996370 11.04 7.675945 1262.500 1.252 1.252 0. S99766 31.32 6.944644 1264.C00 1.;66. 1.266 0.9499e9 11.64 9.97c?47 1205..00 1.;82 1.26] 0.9919f.S 12.03 11.916746 12R? .000 1.299 1.298 0.9eas617 12.46 14.642149 12@%.000 1.324 1.332 0.9)5ý095 13.34 27-3839ýo0 1 290.0CC 1.35) 1.370 0.787949 34.02 18.ld.57851 1240.500 1.36952 1291.00f, 1.410

44

S V

is SEPT. 1904

spFCZpfpNO5. 3100 MANUAL

Paa,, 50 LUF Pair. - 85 Lbf F * 0.100

Res.473 in. W-2.050 •n

P' CYCL I AAct deltea dao/nO COUNI .3n In NC " Isloin 0 J n/cy-- ------- ------ 7.. . . . . . . . . . . -- ----- ------------------------ .......... ---------- . .. .. .. •. .

1 0.001 0.6072 50.000 0.6273 90.000 o.6474 120.000 0.471 0.672 0.999061 6.81 0.1578s 140.000 0.689 0.699 0.999390 6.97 0.9770* 15o.000 0.700 0.700 0.998059 7.06 0.95357 160.000 0.711 0.710 0.998721 1.16 0.9665* 175.000 0.726 0.72.3 0.997598 7-.30 0.99359 190.000 0.738 0.730 0.997610 1.41 1.0055

10 205.000 0.752 0.753 0.996533 1.54 1.053211 220.000 0.770 0.770 0.990480 .71 1.118922 234.000 *0.783 0.701 0.998952 7.84 1.178713 240.000 0.793 0.793 0.997202 7-.94 L. ;854 ., ..14 250.000 0.805 0.806 0.998367 8.06 1.359.15 260.000 0.819 0.620 0.(98634 S.;1 1.419.16 270.000 0.#37 0.836 0.997059 6.41 1.511817 277..000 0.847 0.847 0.998974 6.S2 1.517718 284.000 0.50l 0.657 O.995619 8.64 1.602529 291.000 0.867 0.067 0.996954 8.74 1. 79 2420 298.000 Q.878 0.679 0.998S06 .0.7 2.004621 305.000 Q.894 0.894 0.998655 9.06 2.28.6622 312.000 0.912 0.912 0.994617 9.29 2.369423 311.000 0.927 0.92S 0.995004 9.48 2.582624 322.000 0.939 0.930 0.991418 9.64 2.815125 327.000 0.947 0.952 0.991969 9.75 2.921227 332.000 0.967 0.977 0.990767 10.02 3.1183727 335.000 0.987 0.977 0.991350 10.21 3.113826 341.000 0.990 0.997 0.995864 10.45 3.1446 . -29 344.000 1.004 1.00L 0.99681S 10.58 3.13120 347,.000 1.014 1.014 0.998427 10.73 1.0556

31 350.000 1.025 1.024 0.998565 18.91 3.221532 353.001 1.034 1.033 0.997364 11.06 3.345133 359.00), 1.052 1.053 0.998471 11.37 3.752934 36S.00i 1.076 1.077 0.999613 11.60 4.543435 366.0t 3 1.092 1.091 0.999424 12.11 5.157236 371.00t' L.106 1.107 0.996148 12.39 6.009137 374.000 1.124 1.125 0.997470 12.76 7..76338 376.OCO 1.139 1.140 0.996377 13.09 9.159039 37,.C(0 1.157 1.159 0.997654 13.50 11.226040 379.0.0 1.169 1.170 0.997924 13.79 12.347141 38O.Orn 1.186 1.182 0.984431 14.;l 16.101942 381.0( C 1.197 1.198 0.987483 14..0 20.09C743 301.o( 0 1.212 1.218 0.986458 14.91 29.1631 F744 38 3. Or 0 1.249 1.248 0.995571 16.OC 42.488445 383.5CC0 1.266 1.271 0.996559 16.55 54.9031- -46 383.8(10 1. ;69 1.289 0.991358 17.35 66. 155647 4,4.1U0 1.306 1.312 0.96136? 17.98 113.204448 384.2(0 1. 317 1.323 0.939895 18.41 184.171049 3A4.3N(0 1.329so 384.400 1.36351 384.450 1.,93

45

4"..• .

-0 0

SPECIMEN N(. IAI

... a I 16SO LP' PFai r 10', Lip v a 0.100

0.468 in. • .5

PT CICL' A-cer Aug de1t&F doldnI COUilM in in Nc Itst'r ,uin/cy

S, s.ooc *.ss.4 .•,o •• .,1i••' .2 20.000 0.6292 30.000 0.654* 69.00C 0.69? 0.692 0.948700 0.? 3.11490s 42.000 6.780 0.17" 0.98476 10.90 3.16080 52.00C 0.742 0.742 0.996490 9.29 3.5411 .17 60.000 0.781 0.751 0.998176 9.40 3.61695 69.000 60.7 0.716 G."0079 9.77 4.19129 74.000 0.010 0.607 0.996440 10.13 4.756010 77..0Cc 0.821 0.622 0.997394 16.07 5.3066-.33 60.000 0.836 0.836 0.996250 10.47 S.786 -12 64.000 4.960 0.061 0.999275 10.51 %.209913 60.000 0.877 0.876 0.999062 11.0! 5.3379 V..014 8%.000 0.667 0.664 0.998936 11.34 9.35043s 0D.50C 0.894 0.894 0.996531 11.33 9.362316 &S.000 A.904 0.903 0.9902:2 11.46 9.714317 to.COC .1 0.914 0.9996s6 11.60 10.10601s 91.000 0.924 0.92? 0.906732 11.76 11.20;419 92.000 0.934 0.930 0.976759 11.94 14.34210o 93.500 0.949 0.95? 0.979999 12.19 2S.5162

21 U4.500 0.975 0.978 0.994562 12.65 3%.132022 95.500 1.016 1.020 0.995546 13.43 55.849523 9,..200 ].064 1.064 0.9P0646 14.45 02.391324 96.700 1.093 1.111 0.966720 15.13 121.406325 9%.000 1.132 1.155 0.954722 16.13 199.21S526 91.100 1.170 1.172 0.967104 17.•2 309.776927 97.200 1.19. 828 97.250 1.23129 97.300 1.245

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46

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