Aviation Fuel
Short Description
Aviation Fuel...
Description
AVIATION
•FuEL "PROPERTIES
.I.
Lu
•
REPRODUCED FROM BEST AVAILABLE COF'tý
-
Coordinating Research Cc 10
r
CRC Report No. 530
"
.9 "COORDINATING RESEARCH
COUNCIL
INCORPORATED I1D5PERIMETER CENTER PARK WAY
3
ATLANTA.
SUSTAINING MEMBERS
GEORGIA 30346
(404) 396-3400
,.mericon Petroleum Institute Society of Automotive
Engineers, Inc.
APPROVED FOR PUBLIC RELEASE, DISTRIBUTION UNLIMITED
HANDBOOK OF AVIATION FUEL PROPERTIES
","
In approving this Handbook, the appropriate Committee of the Coordinating Research Council, Inc. has not investigated or considered patents which may apply to the subject matter. Prospective users of this Handbook are respon-
L
sible for protecting themselves against liability for infringement of patents,
I.'•
Prepared by the Coordinating Research Council, Inc. "I
~DTIG 18
LECTE
sEPo06198
Orders for additional copies should be addressed to: Society of Automotive Engineers, Inc. General Puiblications Department 400 Commonwealth Drive Warrendale, Pennsylvania 15096 APPVROED FOR PUBLUC RELEASE; DISTRIBUTION UNMLIM5'Ti,":
FOREWORD
"Thepurpooe of this document is to provide a convenient source of information on properties of aviation fuels for reference use. The data presented hereim have been compiled by the CRC Aviation Handbook Advisory Group from the latest known sources on each particular subject. Where conflicts arose owing to discrepancies in source material, they have been resolved
by decision of the Group. The references cited document the source of information, even though in many cases those references are no longer in print. This document was made possible by the contributed efforts of Industry and Government personnel considered experts in their respective fields (Appendix A). Financial support for its preparation was provided to the Coordinating Research Council by the U.S. Air Force as part of Contract No.
DAAK70-81-C-0128.
Acces.s
XTIS
t
Aoe ni 0 For R&-,,..
DTIc TAB
Unannounced
Justificat ion__[ .-•tri
.
but i on/".
Av__i~labil it y Codes and/oCO-Y-
a /or Aviit Speoial
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Os'lo XINSPECTED/
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9
",
TABLE OF CONTENTS Page
K SECTION 1. 1.1
'DESCRIPTION OF FUELS/ 2
'SPECIFICATIONS;ý ...........................................
1.1.1' Aviation Gasoline (Av Gas).................................. 1.112-tubine -F~uels, ........................................... 1.1,3ýMissiie FueIl......................3 1.2
2 2
ý.\COMPOSITION OF FUELS. .................................... 1.2.1 Tiurbine Fuels
.)......*
........
...
*..*..
*........
10 ...
.....
10
...
1.2.2ý'Hfyd-roc'arbon Missile Fueilsy ..................................
SECTION 2. 2.1
,~ULPROPERTIES' .."FUEL
2.1.1 2.1.2 2.1.3 2.1A4 2.2
15
20
Density--';..........................20 Relative Density (Specific Graviy ity).................. Thermal Expan~ion .................................... ,.. Unit Mass of Fuels........................................
.)VISCOSITY,')
2.3
DENSITY'..................................
.. . . . . . . . . . . . . . . . . .. . . . . .
SRFAC TENSONJ......................................
2. ~OAiLT'.....................
-
............. *
.......
2.4.1 ASTM D istillation ..................... \2.4.2 True Vapor Pressure...................................... 2.5
2.6
:LOW-TEMPERATURE
PROPERTIES"
-74ýHERMAL PROPERTIE§ý 2.6,1 2.6.2 2.6.3 2.6.4 2.6.5
............
J.......................................
Specific Heat ..... ..... ,..................,.... .... ....... Thermal Conductivity . ..................................... , Enthalpy ............................................... Heat of Vaporization ................... .................. Heat of Combustion (Specific Energy) ............... ,.,........
iim
20 21 21 33 3 4 41 41 49
52 52 52 53 53 53
TABLE OF CONTENTS -(Continued)
SECTION 2.
-FUEL PROPERTIES-..(Continued)
2.7
ELECTRICAL CHARACTERISTICS;..............64
2.8
LA2.83.2
K
Pg
29
2.7.1 Dielectric Constant (Permittivity)............................ 2.7.2 Electrical Conductivity....................................
64 64
F_'LAMMABILITY AND IGNITION CHARACTERISTICS .....
70
2.8.1 Flammability Limits versus Altitude .............. u...... Flash Point.............................................. 2.8.3 Effects of Dynamics on Flammability Limits....... 1............. 2.8.4 Effect of Air Release on Flammability Limis.it........ 2.8.5 Minimum Spark Ignition Energy of Fuels ..................... 2.8.6 Autoignition Temperature ..................................
70 70 74 74 74 80
BUL
8
MDULSA...........
.........
...................
2.10, ýSOLUBILITY OF GASE~i8 2,11 k'\SOLUBILITY OF WATEp
vo
.....
......
9
2,12 'ITHERMAL OXIDATION STABILITY)...............98 2.12.1 Test
Deie
98 99
...................
2,12,2 Effect of Deoxygeriation
............
*...
..
*........
..
2.12.3 Effect of Soluble Metals on De'posit Formation 2.12.4 Effect of Metal Surfaces on Thermal Stability .. 2,12.5 Effect of Fuel Additives on Deposit Formation ................ *..~,.*.............. *......
,.
SECTION 3. 3.1
~USER PROBLEMS;
100 100 101
*
K\FUEL CONTAMINANTS,".
......................
,...
.........
,..
105
1-2
3.,11 3.1,2 3,1,3 3.1.4 3.2 3.3
F.'~~3..
Gas Contamination..i Water Contamination .... ,......,............ ........... Microbiological Growth .............................. Solid Contaminants ...... .......................
\FUEL LUBRICITY;:.............. -
..................
105 105 107 108 1
MATERIAL COMPATIBILITY,,..........................*
ill
3.3.1 Metals........................
ii
332Packing
and Gasket........
................
...... ..... ,,
.,....................
11
Lubricants,................................1 3.4 'ITOXICITY.....................
....... ....... .......
112
TABLE OF CONTENTS-(Continued) Page LIST OF TABLES Table Table Table Table Table Table Table Table Table Table Table
1 2 3 4 5 6 7 8 9 10 11
-
U.S. Military and Commercial Aviation Gasoline Specifications............ Commercial Turbine Fuel Specification............................ U.S. Military Specificaticns for Turbine Fuels ........................ U.S. Military Specifications for Turbine Fuels .......................... U.S. Mitary Specifications for Missile Fuels........................... U.S. Military Specifications for Missile Fuels ........................... Low-Temperature Properties of Aviation and Missile Fuels ............... Typical Flammability and Ignition Properties of Aircraft Fuels ........... Typical Flammability and Ignition Properties of Missile Fuels ............. Fuel Thermal Stability Requirements ................................ Effects of Metal Concentration on Thermal Stability at 260C ............
-
-
-
SL.
4 5 6 7 9 50 71 71 102 102
LIST OF FIGURES Figure Figure Figure Figure Figure
1 2 3 4 5
-
Figure 6
-
-
Figure 7 Figure 8 Figure 9 Figure Figure Figure Figure Figure Figure Figure Figure
10 11 12 13 14 15 16 17
-
Figure 18
-
Examples of Hydrocarbon Compound Types Chemistry of High Density Hydrocarbon Missile Fuels................... Typical Density vs. Temperature for Aircraft Fuels ..................... Typical Density vs. Temperature for Missile Fuels ...................... Relative Density vs. Temperature (Max., Min., Typical) - JP-5, JP-4, Jet B ...................... : ........................ Relative Density vs. Temperature (Max., Min., Typical) - Jet A, Jet A-i, JP-8, JP-7 ......................... Relative Density vs. Temperature (Max., Min., Typical) - Therm ally Stable ............................................... Relative Density vs. Temperature (Max., Min., Typical) RJ-5, RJ-6, RJ-4 ............................................... Relative Density vs. Temperature (Max., Min., Typical) JP -9, JP.10 ................................................... Thermal Expansion ................................................. Unit Mass of Aviation Gasoline ...................................... Unit Mass of Turbine Fuels .......................................... Typical Viscosity vs. Temperature for Aircraft Fuels ................... Typical Viscosity vs. Temperature for Missile Fuels ..................... Typical Surface Tension vs. Temperature for Aircraft Fuels . Typical Surface Tension vs. Temperature for Missile Fuels ............... Typical Distillation Curves - ASTM D 86 (Jet A, Jet A-i, JP-8; JP-4, Jet B; Av Gas) .........................................
Typical Distillation Curves
-
11 17 22 23 24 25 26 28 27 28 29 30 31 34 35 38 39 43
ASTM D 86 (JP-5, ,JP-7,
Therm ally Stable) ................................................
.........................
iv
44
-"
K
I
TABLE OF CONTENTS
-
(Continued) Page
LIST OF FIGURES - (Continued) Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure Figure
19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35
-
Typical Distillation Curves - ASTM D 86 (JP-9) ....................... Vapor Pressure - Aircraft Fuels ..................................... Vapor Pressurr - Missile Fuels ...................................... Typical Specific Heat vs. Temperature for Aircraft Fuels ................ Typical Specific Heat vs, Temperature for Missile Fuels ................ Thermal Conductivity of Hydrocarbon-Based Fuels ...................... Enthalpy Diagram, JP4 ...................................... Enthalpy Diagram, JP-5 ............................................ Heats of Vaporization for Various Hydrocarbons at 1 Atm ............... Net Heat of Combustion - Aircraft Fuels ...... Net Heat of Combustion per Unit Volume - Missile Fuels ............... Dielectric Constant vs. Temperature for Typical Aircraft Fuels ......... Dielectric Constant vs, Temperature for Typical Missile Fuels ............ Typical Range of Conductivity vs. Temperature for Aircraft Fuels ......... Fuels Flammability Limits vs. Altitude ................................ Flash Point of Jet A and Jet B Blends ................................ Effect of Tank Dynamics on the Relative Flammability Limits of JP-4, Jet B, and Jet A, A-1, JP-8 ................................. Effect of Air Release on Flammability Limits of JP-4, Jet B and Jet A, A-i, JP-8...,........................................ Minimum Spark Ignition Energy at 1 Atm, Pressure for Aircraft Fuel Sprays ..................................................... Minimum Spark Ignition Energy at 1 Atm. Pressure for Missile Fuel Sprays ............................................. Autoignition Temperature - Av Gas ............................... Autoignition Temperature - Turbine Fuels ......................... Bulk Modulus vs. Temperature and Pressure for Typical JP-4 and Jet B ...................................................... Bulk Modulus vs. Temperature and Pressure for Typical JP-5, Jet A, Jet A-1, JP-8 ....................................... . Solubility of Air in Aviation Fuels.......................... ...... Solubility of CO 2 in Aviation Fuels ................................... Solubility of 02, N2 in Aviation Fuels............................. Solubility of Air in Missile Fuels ................................. Water Solubility vs. Temperature for Aircraft Fuels ..................... Water Solubility vs. Temperature for Missile Fuels.................... Separation of Contaminants - Water and Rust .........................
-
-
Figure 36 Figure 37 Figure 38 Figure 39 Figure 40 Figure 41 Figure 42 Figure Figure Figure Figure Figure Figure Figure
43 44 45 46 47 48 49
-
45 46 47 55 56 57 58 59 60 61 62 66 67 68 72 73 76 77 78 79 81 82 85
'
86..... 8 89 90 91 92 95 96 109
".
V..
APPENDICES .
Appendix A
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Membership of CRC Advisory Group on the Aviation Fuels Handbook .....
A-i / .'
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4. .
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L
SECTION 1 DESCRIPTION OF FUELS *FUEL SPECIFICATIONS *COMPOSITION OF FUELS
r-0
1.1
SPECIFICATIONS Aviation fuels and fuels for air-breathing missile propulsion are characterized and controlled by specifications. In the case of fuels for aircraft, the specifications are based more upon usage requlrements and less upon the detailed chemistry of the fuels. The one composition requirement common to all aviation fuels is that they shall consist completely of hydrocarbon compounds except for specified additives. There are, however, some limits on particular hydrocarbons such as aromatics and olefins primarily due to performance factors. The system demands are still the primary determinants of the requirements and include such items as fluidity, combustion properties, corrosion pro"tection, fuel stability, contaminant limits, additives for various purposes, and other miscellaneous properties. The missile propulsion fuels, unlike the aviation fuels, are primarily controlled by specific chemical composition. In this case, the chemical composition has been tailored to satisfy the system usage demands. Additives are also specified to meet certain requirements. Where applicable, NATO symbols have been included.
r
1.1.1
Aviation Gasoline (Av Gas) Specifications for aircraft reciprocating-engine fuels are found in Table 1. There are three grades of fuel-80, 100, and I00LL. In this case, there is no requirement for the and 115/145. The commercial specification as described by ASTM D 910 also covers three grades of fuel-80, 100, and 100LL. In this case, there is no requirement for the 115/145 military fuel, but a Grade 100 of higher lead content is permitted. The low lead, 100LL, is identical in lead content to the 100/130 military grade. The grades are determined primarily by octane or performance number.
1.1.2
L
Turbine Fuels Turbine fuels are in extensive use by both military and commercial aircraft. Although similar, military and commercial fuel differences warrant separate specifications.
' 1.1.2.1
Commercial Turbine Fuels The specifications for these fuels are found in Table 2. There are two basic fuels included: a kerobene type and a wide-cut (kerosene and naphtha mixture) type. ASTM Jet A fuel is used exclusively in the United States with Jet A-1 being the primary fuel outside the United States. The International Air Transport Association (IATA) guideline specifications are basically the same as ASTM Jet A-1 and Jet B
*..-V
:. .....
....
.
.
-,;,V.
....
.
*
.... 2
... 7
"4.2 '
-
1.1.2.2
U.S. Military Turbine Fuels There are several turbine fuels in use by the military services. This is due to the different operational needs of the services, or to specific applications requiring special fuels. The primary fuel for the U.S. Air Force and Army is the wide-cut JP-4 fuel that meets operational requirements and reflects a broad availibility. The U.S. Navy, particularly for carrier safety, relies on JP-5, a high flash-point fuel. JP-7 and Thermally Stable fuels (TS) are used by the Air Force for specific applications in which high thermal stability is required. JP-8 is a kerosene-based fuel very similar to the commercial Jet A-i, and is under consideration by the Air Force as a replacement to JP-4. The specifications for JP-4, JP-5, and JP-8 are found in Table 3. Those for JP-7 and thermally stable kerosene are shown in Table 4.
1.1.3
Missile Fuels Missile fuels included in this Handbook consist of pure hydrocarbons or mixtures of a few JP-9, hydrocarbons for use in air-breathing missile engine;;, These include RJ-4, RJ-5, RJ-6, and JP-10,
1.1.3.1
Ramjet Missile Fuels
Turbine Missile Fuels JP-9 was an Air Force fuel which was specified for use in the Air-Launched Cruise Missile (ALCM). JP-10 is a fuel meeting the - 65oF Air Force operational requirement, and has replaced JP-9 as the operational fuel for the ALCM. Table 6 outlines the specification requirements for JP-9 and JP-10.
.
6
"
.
',.
RJ-4, RJ-5, and RJ-6 are fuels originally developed for ramjet-powered missiles, RJ-4 has been selected by the Navy for the Sea-Launched Turbine-Powered Cruise Missile. RJ-5, a high-density fuel, was originally specified by the Air Force for the Advanced Strategic Air-Launched Missile (ASALM). Due to unsatisfactory low-temperature properties, RJ-5 has been replaced by RJ-6 for use in the ASALM. Specifications for these fuels are found in Table 5. 1.1.3.2
.
..
.........-
3
TABLE I U.S. MILITARY AND COMMERCIAL AVIATION GASOLINE SPECIFICATIONS '..S.Navy 811 .GOf72F.Anaid. I mintASTM D1910I Jo 13 Maurch1970 1)181 80187 1100130 Av Giasoline, Av (laaolint' Red Blute(3)
Iso-.ilig \gecV1QI Spveofickatin: Revision Daute: Gjrade 1)etignatltta: FuelIType: Color: COIMPOSITION
Sulfur (wt Artomatics (vt) l w
VoLATILITY
Djistillation Temp. 1017 Itee (11C) 401% Rut, (11C)
Mb MAX. MIN.
0.06
0.051 0.11.
115/140 Av G;.asoline Purple
ASTM Test Meathd 1) 1290or 0) 2622 1 0 1)1:11 Dpoo
0ý0( 5.0
or 1) 2297
REid h'LIIiY CIM USIIN
Pointr(1C
'Evung1aporte 'Ceis idl uk, ofCal'ol ".)M MJIkglato (HI La ol Goio.'ravity. O P rauo
MLIIY lixtur
uPeoihnt V g
ai
COMBUSTION 2 hNot at of0"C)nkfu MTAIkLIT (Btunti)( (MIN. 1111 hr.00 Al'~mvg'ruvit Prouc CO TMI
MX t
1017
uCper SrpCroin
%'('I.~l Ch angeo.) reortednot ive lmt dokvlue B2ohlgnel Dy b ATe
751 751
7in 76
1)8a
7
MAIX, -6011 X.t6n~i MIAX. 13.(18111) M 7,(10
!l
MIN AX,1
-to0
-188
7
71
15 8 0
43rA8,0)
-136)11 44.tl1,10 6)41o
2 D(01 28701111or1 8
14
1)21800
7,0,0
1,15
44ing90 91800
) 4 r 1)8(11o
3.0
3.0
1.0f
1.)2701 2 )1
MAIN,
S7
218
14
DO1W
MAX.
0.1
I,
1.2
1)2309,o )24
MAX'
(ml)ecaeRtn
1'reelptatuni)
N~lTF.~ (1 T
75 75
xatuen iTl Av~iain Rat/ingml MIN, Interac Rating.RAich22 Mil.thune
COROIO
MIN. at MAX. ti
(m/100 MAit'0
MAX.
8 8
2.0.20D87
2
2-
etod1 210 Ar MlAX. llcao
(2rKovk valesteob 1wmltarnd y ASTMoMthod Dt70irotoroo
'22D19
Nnhrto 1o61r Aitn0.71atno, 1ta Table
Opvfctalne Nurmters lea
contert 1110iato t listhe ause gs
lool~l.l~l mnamely 11.501 g/luIer MAX. Ilowaevr. this ctommercial gradet1110 Is ,ohtreti green: to,) has teat) etttoltl
23o92T11)
Tableat t ofr miitr StM tf
1.12g/blet MAX.
90lwtlll
TABLE 2 COMMERCIAL TURBINE FUEL SPECIFICATIONS I -ung
'U
.\
A." NI
iii 1
ysolD t
Iim
radv kvsigrotioII:
ilw
1,
Doetor Test. N -Nviiauiv,'
I
1A .1 A
1(2,2
A 12.)
AlII
,In. '9
N
N
N
N
I
1.
1111,2
(A
slulfur, Tlotal oyt2 -!Ill
II
I
Ii) It
4311I 'II 1)1121111)0
11)MU V1 L.A!)LIlY
Disti(ltllatio Ilillp, (liii 11)1("C) 201%, Rve("C() fill% iItt- V"IC P11014, liP ('11) Flinl) lit,4(1,)
P.)
FLUIlIlY *
MAX. MAX. MAX. MAX.. MAX.
3.0
.1 .
I.r
1.6
jrl
VII(lior I'128)sure.W8C(kill)
MAX.
F~reezing Pl'411I"G) Viscosi~ty(D -. 1112Ci~t)
MAX. MAX,
-41) (2) 9
-4210
-47 8
-50
-
MIIN.
42.8
42.8
42,8
42.8
MIN.
45 25 .11(4)
llColio 81(2 tlri
MIN. MAX.
lirg a 1I81WC)
MAX,
1.2
28 21
21
'(I6 '2 Il 81
25
211
MAX. MAX.
-,:3
MAX. MAX. MAX, MAX.
7 Ill
Witily, ReioiniI Inturfitep2 Witter Helm-t~ili Sepalraionlu
-15-7 0l.75017-b.801',
I
JVrOT TupClor (21112(81(
46 25 (4
~
25
211 11
1) :12,11)1) or
7
7
7
1) 3s81
-
11)
1I
1Wit
2
2
-
Ill
Agemonlyol Optioln
011111 CIt
MlectrikuI (IoolucLivly (uN/mI) (6)
21)420
~ ~ ~t25vlI~~~(2
0)~ cotinn
lsSoePin
0MN
no04f))
li.421
it
rnIXd
Nil tivii iy Jill 14111111111 If Kuppl(IIr ilintiflill 2011.
8MNnt
vshpe
fsp.vi
oiisutr
V' ttnv lvFadtmxaue(tdlvr toarrf fwtsui.tmtv.i s.i (1)-A~
toeIoo
0MNls
11111, JIMF Ill 71
(31)1 ito (1))
) 1)1I) 1110114
154
1017 13 1 2)1) I21 28)) 21))
AgVU1llvinwit. lptIill Option Option Agreement~ AgrIelintlvtt Agl'vemnte (71
Nu'VE8: (1) This isnot, it HopoQlIcist(1lt, Ijslt (;I2110121M't-rial, (21 lot A. 11 ts H 8im1012k&'tIometi'.l-ypi, but F'ovesliig Point Is -o.4711C MAX.
(4
17o1,34
1)2282 ort 1) 1405 (g) 1)174(1 1)13(22 1)1840 1)1:41)
2
Aniilelltig AIIIFX(luxidn Iti~llillltlr
46
26 2I(2)
1) 23818) 1)4452
1
I
ADITIVES' 1.
ti()2)
--
I
D1287
1) 12119 1) 3223
I
I
2
Il2a1(
'16.57 1ý72)i 0.,750l7.0I,8011I ll.77MI2.1l82118
I
IFTPOT All (11111Jig)
(8)N'1AmINANT8 Vx~mitonltu (J~1lingIV 118ill I'arIlvula111m 1mg/Il
4CorrosIIion
30012
37,8 31-5) 01753-0I.83118
123)
i1ixg) Rp 21111
M I N.
LuhlmoIIott(r Nil.
Il(11)
1) 8)) I-
MAX,
or Smoke1Polint or1Nap1hililtkivi, (vIII 4)
.911AIILITY
2014 1-13.3) Ip 7.
Hilt
Los (%ill %), 8 ) 1L'1li PointI (TC) (1traviky, 'A I'i (1(1212) k-l(,ulivio Density II p,2c)
8111 IW13T11N Net1 licii) of 122411(11,1IJ1kltl)
(2
20-1.4
r 1)I26122
8MN
.4.
a
isipdi
uplrntfvsutr
60-3001
1)
2)124lor 1) 11114 2741
TABLE 3 U.S. MILITARY SPECIFICATIONS FOR TURBINE FUELS MIIL,'1'.0024L-A nid I It! June1090)
)4ciivatulloti: RHv,~viru Date: Grade Desiglttstin.
F'uel Type:
coil'M sITIIIN
VOLATILITY
11)2810 Limuits ill purenltheses)
Wide-cut M1 AX. MAX, MAX .. 0AX. M. MtAX.
0.015 26,0 ) 0.1001 0.4
6.0 nom
('ulor, Soybolt
MAX.
Uistillutiuu Temp. lnit. BP' ("0) Twill,. 10%,Her (112) 2044% er (,'2) 1104%Hee("6) 9140))Hee(WC) FilnalHP (0c) HReildue(vol %) (fur D 81)) lose (VuI 11')(for 1)Hill ExpiviaMveheas,peorcent
0.0011 0.4
1) 42412 D0~ 13 Ia9t 1319 1323 1) 128W40)28847/
Rvport
Relport
Report
D16141
MAX,
Report
1) 8,"D 200
Re-port 146(130))
Report 2)05(1860)
Report
MAX. MA X.
Report
Report Report
MAX, MAX. MAX, MAX. MAX. MAX.
Fluch PI'u)., (10 itavlty. 'API (1.;KC) D)ensity, 1I-C (kigi)40') Viipxr Pressure (37.8'C)
MAX.
F"reezing Point, TC(F)(
MAX. MAX. MIN.
Vise -sity a -20C. (c~t)
COM"USTION
A. -.e-Gravlty Product
1140 (14186 245(2001 270(3024) 1.0 1.0
)11
0.01)6 2
201, 186))
Report Rei~ort 200 (220)
Rel'ort 300 (300) 1,r 1.6 111)1FED~L STI)
50
MAX.
46.57
MAX.
7182788-840
14-21 (2.U.8.01 -581(-72) -
0200
410 3041.4
37.51 770,840
(BtWlb)
D493 (2) 1 D 1298 1 1208
1)123i'1)2551
.-
-46 (-51) 8.0
-00 (-58) 8.0
D32088
D)440
4500
D)1405 D)232(1D 03338) 1) 240(0) 1) 122
or Net Ileat uf Comb., Md/kg Smoke point ur Hlydrogen (lontunt (wt %
Meth~od ASTM IT011 791
0.5 11.0 5.) .40,01 0.3
hI's (pmi)
FLUIDITY
4 April W181) ,l'*e'it .111. Ieriiiuene
KEro~eee
A'!ldiy, Toald iun K(4lt)i Arotmatics (Vol '%) 01,-fins ,r,4 %) Sulfur, Mercuptaii (w. 'V.,) 1) Sulfur, Total lW '%)
.
Mil.T.310 3IA.Aind. I
,31 -'4
M IrN.
42.8 (18,400)
42.61110,800)
42,8 (18,400)
NIIN, MIN.
20.0 1.41
19.,0 13$,5
10.0 13.0
lb
lb
lb
1)1,00
MAX. MAX.
20
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