Analysis of combustion processes in a gun ib

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ANALYSIS OF COMBUSTION PROCESSES IN A GUN
INTERIOR BALLISTICS
T. W. H. SHEU
a
& S.-M. LEE
a
a
Institute of Naval Architecture and Ocean Engineering, National Taiwan University , Taipei,
Taiwan, R.O.C
Published online: 07 Mar 2007.
To cite this article: T. W. H. SHEU & S.-M. LEE (1995) ANALYSIS OF COMBUSTION PROCESSES IN A GUN INTERIOR BALLISTICS,
International Journal of Computational Fluid Dynamics, 4:1-2, 57-71, DOI: 10.1080/10618569508904518
To link to this article: http://dx.doi.org/10.1080/10618569508904518
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Comp. Fluid Dyn., 1995, Vol. 4, p. 57-71 Q 1995 OPA(0versea.s Publishers Association)
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ANALYSIS OF COMBUSTION PROCESSES
IN A GUN INTERIOR BALLISTICS
T. W. H. SHEU and S.-M.LEE
Institute of Naval Architecture and Ocean Engineering.
National Taiwan University. Taipei. Taiwan. R.O.C.
SUMMARY
Thispaper presents the numericalsimulationofthegas-solidcombustion physics inagun tube with a mobile
projectile by means of a flux-corrected transport nonlinear filtering scheme. Thc analysis is based on
a one-dimensional formulation of the two-phase flowfield with the space-sharing interspersed continuum
assumption. Apart from the Nobel-Abel equation or state account the interphase drag and intergranular
stress between the solid-gas phase are taken into account. The computer code has been used effectivelyto
study the pressure-wave propagation and flame dynamics in a gun barrel containing granular solid
propellants.
KEY WORDS: Gas-solid, mobile projectile, flux-corrected transport, combustion.
1. INTRODUCTION
The gun-interior ballistics involves many intricate physical and chemical processes.
Investigation of such phenomena is difficult to perform experimentally and subject to
a high degree of uncertainty and inaccuracy. Recent advances in computer hardware
and solution algorithms have made the numerical study of the two-phase gun interior
ballistics possible.
Themajor physical processes involved in a gun interior ballistics during the transient
period were well described by Kuo.' The chemical processes following the ignition of
the solid propellant usually occur within a few milliseconds. The penetration of hot
gases, produced by the combustion of the igniter near the front end of the gun barrel,
into the void region leads to the ignition of solid granules by convective heating. The
granule compaction and rapid pressurization are then set up during the subsequent
ballistic cycle.The ignition front accelerates due to the resulting pressure build-up. The
ignited propellants release hot gases which then move forward by the developed
pressure gradient and thus ignite more propellants. As a consequence, a steep presure
gradient is established inside the combustion chamber. These accelerated gaseous
products finally cause the projectile to move. The flame spreading and possible
shock-front formation in porous propellant charges are, without doubt, of importance
in the design and analysis of propellant loading and combustion chamber configur-
ation.
Numerical studies of the physics of combustion in a gun combustion chamber have
been attempted in the past two decades. Most of the computer code^^-^ were developed
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58 T. W. H. SHEU AND S.-M. LEE
within the context of a one-dimensional analysis. Recently, extension to multi-dimen-
sional analysis for such problems has been made6
- S.
It is well established that the direct application of central-difference schemes to treat
steep-front waves may cause numerical oscillations in regions having strong gradients
during the ballistic cycle. The first-order accurate Lax scheme? offers positivity-
preserving monotone solutions but sacrifices the solution accuracy near the high
gradient region. Considerable numerical dissipation is added and it may sometimes
lead to erroneous predictions of the real physics. Improvements on the solution
accuracy can be easily made by using a higher-order discretization scheme, such as the
Lax-Wcndroff'scheme!", but this usually produces oscillatory solutions in regions with
now discontinuities. Accuracy and positivity seem to be contradictory to each other
and mutually exclusive. This difficulty is a crucial issue and is directly related to the
solution quality. It motivated researchers to develop a high-order non-oscillatory
solution method for capturing shock-like solutions. Historically, a large number of
high resolution schemes11-13 have been developed and successfully applied to circum-
vent the above-mentioned numerical difficulties. For a further discussion of modern
advection schemes the reader is referred to!", The present study focuses on the FCT
technique. The idea behind FCT is to combine a high-order scheme with a low-order
scheme in such a way that the high-order scheme is employed in regions where the
variables under consideration vary smoothly, whereas in regions where the variables
vary abruptly these two schemes are combined through a nonlinear combination of
diffusive and anti-diffusive fluxes. The resulting discretized equations can maintain the
positivity-preserving property.
In the following sections, a detailed theoretical formulation of the physical processes
is first given, followed by a bnef description of the FCT scheme employed. Finally, the
analysis isapplied to study the two-phase chemically reacting now in a gun combustion
chamber with a moving projectile.
2. FORMULATION
The numerical prediction of transient combustion processes in a granular-propellant
bed is made by solving the following conservation equations for a two-phase mixture.
These equations are formulated by assuming the gas and solid phases are inter-
dispersed and coupled through appropriate interactions. Each phase is treated as
a continuum. The conservation of mass, momentum, and energy for the gas and solid
phases can be represented by the following expressions:
Gas phase
Solid phase
(1)
(2)
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COMBUSTION PROCESSES IN A GUN 59
Table 1 Dependent variables and source terms of the gas and solid phase equations
Gus pl~rrse Solid pl~use
b st 4 s 2
Moss I filcomb 1 -
%
,
h
where Rl is the porosity of the gas and Rl +R, = 1. The dependent variables and
source terms S in the above equations are given in Table 1.
The Nobel-Abel equation is used as the equation of state for the gas phase1,
where R is the specific gas constant and b is the co-volume. The constitutive equations
used for the closure of equations ( I ) and (2) are described below.
The intergranular stress arises in a packed barrel in which the particles are agglom-
erated. This isotropic normal stress in the solid phase affects the particles only and is
determined by the following ~orrelation.~
where a is the speed of sound in the solid phase. There is no direct contact between
particles when the porosity exceeds a critical value R,.
Il~rerphnse
dray
The average steady-state interphase drag D in the momentum equations is represented
by the following correlation for a packed bed:
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where S = nr~ and V = 4/3 nr~ are the surface area and volume of a spherical particle,
respectively. The interphase drag per unit area F of the solid phase can be modeled by
Ergun's correlation:' 5
F = pu-upl(u-up )!
6
where
1
1.75 for R,:;:;;Rc
, [R2Rc ]
f = 1.75 R,(I _ R
c
) for R, < R, :;:;; R,
0.3 for R, < R, < I
R, = [ 1+ 0.01986C ~cRc)r'
In this study.j'is taken to be 1.4 for the sake of simplicity.
(6a)
(6b)
(6c)
Particle burning rate
An empirical pressure-dependent burning law isemployed to model the particle surface
regression rate under the steady-state condition;"
Z=Bpn
(7)
where the constant B and pressure exponent n are specified for each propellant under
investigation. The mass burning rate of propellant is given by
(8)
where 0v is the fractional rate of change in propellant-grain volume. As far as the
number of burning grains in each cell N and the number of perforations in eaeh grain
fare concerned, the propellant mass burning rate in each cell is given by
(9)
where
~ V(t) = ~(D~ - fD 2)L- ~(L-fJ(t)) [(Do - fl(t))2 - f( D; + fJ(t))2 ] (lOa)
fJ(t)=2Z~t (lOb)
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COMBUSTION PROCESSES IN A GUN
Gas-solid inrerphase heat transJer
The interphase heat transfer Q, arising from the propellant heating, is given by
where h, = Nukld is the total heat transfer coefficient and d = 6V/S is the equivalent
propellant grain diameter. The Nusselt number Nu is given by3.
where the dimension of pressure is MPa.
Molecular transport properties
Sutherland's law is used to compute both molecular viscosity and thermal conduc-
tivity. They are assumed to be functions of temperature and are given bys.
where
3. NUMERICAL MODEL
For the sake of simplicity in describing the presently employed discretization scheme,
equations (1) and (2), written in terms of the strong conservation law form, can be
further expressed in the following symbolic form:
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Apart from the nonlinearity in the above partial differential equation, it is particularly
challenging to analyze a problem involving reaction process. In the combustion
chamber, a shock-like high gradient profile over an extremely short distance may be
formed, even if the computation begins with a smooth initial condition, due to the
energy input through the release or chemical potential. Consequently is important in
the present two-phase flow simulation to adopt a discretization scheme capable or
capturing accurate but non-oscillatory solutions.
Godunov 16 has clearly demonstrated that there is no linear high-order method
which guarantees monotonieity. In this regard, it is inevitable to adopt a nonlinear
discretization method. A large number of monotone discretization methods for
equation (14), are available.':' We can divide them into three categories, namely linear
hybridization methods, methods based on Godunov's algorithm 16, total variational
diminishing (TOY) methods II. Among these, the flux corrected transport (FCT)
algorithm, classified in the first category, is the only one that is applicable to
multidimensional analysis 17. Based on the premise that the present one-dimensional
scheme can be extended to the multi-dimensional analysis, we have adopted the FCT
technique in the present analysis.
In linear hybridization, such as the FCT technique, the results ofa low-order method
and a high-order method are blended in a nonlinear fashion. We first discuss these two
basic schemes as follows:
3.1 Low-order discretization scheme
We adopt the first-order Lax method? to guarantee positivity, which is very desirable
when sharp gradients (or discontinuities) are captured as part of the solution. In the
Lax method, the solution is expanded in a Taylor series about point (x, t) only to the
first two terms and the time derivative are rearranged. This, together with the use of
centered difTerences for the remaining spatial derivatives, yields the following explicit
discretized equation
q'~+I=~[(qn+q'~ )_~(Fn -F"- )J+S~M
_J 2 _J _r l t.x -J+I _J I -J
(15)
3.2 Hiqh-order discretization method
To assure accuracy, we adopt an high-order method in smooth regions exclusively. The
Lax- Wendroffmethod I 0 was developed in the same vein as the Lax method by a Taylor
series expansion. For attaining greater accuracy, we include the second derivative term
(M 2/2)
(iJ2q/iJt 2
)lx.1in the expansion. Replacing the time derivative with the spatial
derivative through (14) yields
(16)
where the Jacobian matrix ~ is defined by d = iJDiJq.
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Using central differencing, the high-order scheme based on the Lax-Wendroff
scheme is derived to be
The Jacobian matrix at thej + 112 location is evaluated by
We denote the Lax-Wendroff solution by q**.
The first-order accurate Lax scheme is extremely diffusive to maintain positivity and
monotonicity. The second-order accurate Lax-Wendroff scheme is less diffusive but
is susceptible to instability in the vicinity of a sharp gradient. To circumvent these
problems, we incorporated a nonlinear monotone mechanism into the formulation so
that the respectiveadvantagesof the Lax and Lax-Wendroffmethods can be combined.
The flux corrected transport technique of Boris and Book13, consists of the following
steps to compute the fluxes at cell surfaces j + 112, for example, from the Lax and
Lax-Wendroff solutions.
(i) Generate diffusive fluxes:
where 5, is the diffusive coefficient defined as
(ii) Generate anti-diffusive fluxes:
where p is the anti-diffusion coefficient defined as
(iii) Limit the anti-diffusie fluxes:
To obtain a positivity-preserving algorithm, the anti-diffusive fluxes in step (ii) are
modified by a flux-correction process. The corrected fluxes are chosen in a nonlinear
manner to prevent the anti-diffusive stage from introducing new maxima or minima in
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64
the solution.
where
T. W. H. SHEU AND S.-M. LEE
T= sgn(fj~1/2) (23)
DO:1/2= T· max [0, min{ T ~qj.!i/2' l[j~ 1/2 1
, nqj.:j/2}] (24)
(iv) The values of qi are given by
q a+l _ q . u _ ! ,ad +!,ad
_i - _i _i+1/2 _i-1/2
4. COMPUTED RESULTS
(25)
Projectile
In Figure I, we define the computational domain as the region between the breech and
the projectile, which is divided into 100non-uniform cells. In the course of the chamber
pressurization, the solution domain is expanded as the force acting on the projectile
exceeds the spindle force and results in the movement of the projectile. The basepad as
well as the center-core igniter normally consist of black powder. Ajet of hot gases is
discharged from a primer, taken to be 16.67% of the length ofthe chamber, to ignite the
basepad and then, in turn, ignite the center-core igniter. The ignition sequence is
modelled by specifying the flow rate and energy. In this study, a bag of M6 propellants
is considered to be uniformly distributed. The initial density of the solid propellant is
assumed to be 98.5Ibm/ft2
• The propellant ignites as its surface temperature exceeds the
ignition temperature, T,ga = 450 K~ For the sake of clarity, the input data issummarized
in Table 2.
O~;;;;--+;;;;;;;;;;:;;;;;;;;;;;;;;;;~
:..
....
....
=~~~~~~~---
IE---......,....,.....,.,..-----*-"'-"-""""---+ 16.67 ft
~~~~
i-I 2 3 4 i 98 99 100
Computational Domain
Figure I Schematic of a mobile granular propellant bed.
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Table 2 Input data
Gun Tube
Projectile
Propellant
Igniter (Black Powder)
Initial Conditions
Diameter
Breech Face
Propellant Bed
Muzzle
SurfaceTemperature
Mass
Density
Elastic Stress Wave
Total Mass
Density
Grain Length
Grain Diameter
Perforation
Burn rate
B
n
Ignition Temperature
Thermal Conductivity
Thermal Dilfusivity
Emissivity
Chemical Energy
Molecular Weight
Co-volume
Plastic Deformation Stress wave
Elastic Stress Wave
Porosity
Ultimate Failure Stress
Yield Stress
Initial Temperature
Chemical Energy
Molecular Weight
Diameter
Co-volume
Thermal Conductivity
Thermal DitTusivity
Ambient Air Temperature
Ambient Air Pressure
Propellant Bed Temperature
Velocity
0.433 ft, (constant)
O.Ocm
2.5 ft
19.I7ft
535 R
100 Ibm
500 lbm/It '
160000 ft/sec
21 Ibs
98.5Ibm/ft
0.0833 ft
0.0375 ft
0.00375 ft
Bp ern/sec
0.2218; p in M Pa
0.7864 (constant)
810 R
0.356E-4 Btu/It-see-R
0.935E-6 ft/sec
o
1607 Btu/Ibm
21.36
0.0173611 ft/lbm
1900 It/sec
3800 It/sec
0.4217 (constant)
1.584E61bf/ft
8.21E5 Ibf/ft
535 R
675 Btu/Ibm
36.13
0.00433 ft
0.016493055 (constant)
0.2E-4 Btu/ft-sec-R
1.0E-6 It/sec
535 R
2116.8Ibf/ft2
535 R
0.0 It/see
Figure 2 shows the calculated pressure distributions at various times. The initial
length of the propellant bed is 2.5 ft. Because of its highly dissipative nature the Lax
method fails to produce physically accurate solutions. The calculated pressure distri-
bution is rather uniform during the entire event; no wave propagation phenomenon is
observed. In view of this, the following discussion is based on the Lax-Wendroff
method with the FCT correction.
Owing to the penetration of the igniter gases into the propellant bed, the granular
propellants near the breach end ignite first, and their combustion products cause a
local pressure increase at t = 2 msec. The pressure wave and its associate flame
then propagate downstream to the projectile base. At this time, the projectile starts to
move since the force acting on the projectile exceeds the friction between the gun barrel
and the projectile. As time elapses, the combustion chamber volume increases because
of the movement of the projectile, thereby causing a pressure decrease starting at
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t = 5 msec. The computed pressure and flame fronts are presented in Figure 3, which
provide useful information regarding wave propagation in the gun tube. The calculated
gas-phase velocity distributions at various times are shown in Figure 4. According to
the pressure profiles given in Figure 2, a vigorous combustion of the granular propel-
lant occurs near the projectile base at t = 3 msec. The pressure gradient established in
the chamber causes a negative gas velocity, with combustion gases moving upstream
toward the breech end. Figure 5 presents the distributions of the solid-particle velocity.
The lag of the velocity with respect to its counterpart in the gas phase is clearly
observed.
The gas-phase temperature is also calculated, since it influences the combustion of
granular propellants. The flame spreading during the initial development of the
combustion process is clearly observed in Figure 6. The maximum temperature takes
place at the breach end at t = 3 msec. This may be attributed to the temperature
recovery effect at that (stagnation) point. The temperature distribution then becomes
more uniform as the projectile moves downstream. Figure 7 shows the calculated gas
density distributions.
Finally, the gas-phase volume fraction is calculated, giving the result shown in
Figure 8. This result serves as a guideline to examine the extent of the solid propellant
15
10
Dis/ance (f1)
(a)
5
, I
- - 3.025£-2 ms
- --oAr-- 2,000 ms
-
~ 3.000ms
-+- 4.000ms
------- 4.510 ms
---e- 5.000ms
-
- ------.e..- 5.500 ms
- v - 6.000ms
~ 6.500ms
-----B-- 9.500ms
I- -
.... -
.....
.~ -
r-"
I- -
, , ,
I.O.dO'
O.O.dO"
o
2.0.dO'
6.0xlO'
i;: 4.0x10'
.....
:.;.
::::.
~ 3.0xI0'
"'
~
0...
5.0xlO'
Figure 2 Pressure distributions in the gun barrel at various times: (a) Lax method, (2) Lax-wcndroff
method with FCT correction.
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6.0~10'
-
-
t 3.025E-2 ms
5.0~10' -2.MWmr
-3 W O m s
4.Wflms
-
-
C 4700mr
-S M W m r
G 4.0x107
-5 5 0 0 m r
;
; -6 f l W m r
-6 5 0 0 m r
s 9500mr
3.0~10'
w
w
2
4
2.0~10'
1.0x10'
0.0X1oD
0 5 10 15
Distance (
/
I
)
(b)
Figure 2 (Continued)
burning. A rapid increase ofthe gas-phase volume takes place near the forward end due
to the burning and forward motion ofthe solid particles, especially in theearly stage of
-
the ballistic cycle. It is interesting to note that in the later phase of the combustion
event, the transient compaction of the granular propellant bed near the projectile base
causes a reduction of the gas-phase volume. Finally, the gas volume fraction becomes
unity when the propellant is completely burned.
5. CONCLUSIONS
A numerical simulation of the gas-solid flowfield in a gun tube is presented in this
paper. The global trend of the combustion physics has been well predicted by the
present computer code. The main conclusions regarding the computational aspect are
summarized as follows.
I . A monotone, positivity-preserving algorithm is indispensable in predicting the
two-phase combustion in gun interior ballistics since an abrupt change in thermal as
well as flow properties may occur. A high resolution solution was made possible by
adding an anti-diKusiveflux.To maintain the positivity of the solution a limiter limiting
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T. W.H. SHEU AND S.-M. LEE
4
-Prn,.r< Fro",
-Flnn,.Fronr
S
.O z
*
I
" t
0
.
W 0.W2 0 . W 0.W 0.WR 0.010
Time (sec)
Figure 3 Time histories of pressure and flame fronts
5 10
Distance 01)
Figure 4 Distributions ofthe gas-phase velocity at various times
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COMBUSTION PROCESSES IN A GUN
Figure 5 Distributions of the solid-particle velocity at various times.
Figure 6 Distribution of the gas-phase temperature at various times.
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T.W. H. SHEU AND S:M. LEE
Figure 7 Distribution of the gas-phase density at various times
~ ~ " ~ ~ ~ " ~ ~ ~ ~ ~ ~ ~ ~
0 I 2 J 4 5 6 7
Distance @)
Figure8 Distribution of the gas-phase volume fraction at various !imes.
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COMBUSTION PROCESSES I N A G U N 71
must be incorported in the solution algorithm to ensure that no new maxima or minima
will be computed.
2. A low-order solution which must be strongly diffused to ensure positivity is
crucial to the implementation of the FCT nonlinear filtering technique.
This research was conducted under a contract sponsored by the National Science Council. Thanks are
cxpresscd lo Mr. H-CChcng, Dircctor ofthe Ballistic ResenrchCcntcr of the Combincd Service Forcc. and
his collcagueswho made this project possible.
R<fere~~ces
I. Kuo. K. K. (1986)Pri1rcip1c.sr,jCor~lhlr.stion,
John Wiley and Sons. New York.
2. Kuo. K. K., Koo, J. H.. Davis. T. R., and Coatcs, G. R. (1976) "Transient Combustion in Mobilc
G:wPermeable Propellants". Acto A.sfror~oufic.s.
3. 573-591.
3. Fisher, E. B., and Graves, K. W. (1972) "Mathematical Model of Double Base Propellant Ignition and
Combustion in thc 81 mm Mortar". Calspan Report No. GD-3029-D-I. Aug.
4. Gouh. P. S.(1977)"NumericalAnalysisofaTwo-PhascFlow with Explicit Internal Boundaries", IHCR
77-5. N:~valOrdnance Station, Indian Head. MD, April.
5. Markatos. N.C. (1986) "Modelling of Two-Phase Tritnsient Flow Combustion of Granular Propel-
lants", I~rt.
J. ~JM~~lfiph~ise
Flow, I 2 (6), 913-933.
6. Gough. P. S. (1979) "Two-Dimensional Convective Flamc Spreading in Packed Beds of Granul;~r
Propcll:rnt". ARBRL-CR-00404. July.
7. Gibeling. H. J.. Buggcln, R. C. and McDonald, H. (1980) "Dcvclopment a Two-Dimensional Implicit
Interior Ballistics Code", ARBRL-CR-0041 I.January.
8. Markatos, N.C. and Kirkcaldy. D.(1983)"Analysis and Computation ofThree-Dimensional Transient
Flow and Combustion Through Granulated Propcllanls", Int. J. oJHeur Tronskr. 26 (7). 1037-1053.
9. Lax. P. D. (1954)"Weak Solutions of Nonlinear Hyperbolic Equationsand Their Numerical Computa-
tion". COI~IIII. (,jPirrt' wid Appl. Mrril~.,
7, 159193.
10. Lax, P. D. ;~ndWendrofl, 6. (1960) "Systems of Conservation Law". Curarn. rf Pwe Appl. Mrrrh., 31,
217-237.
II. tlnrtcn. A. (1983) "High Resolution Schemes for Hyperbolic Conscrvation LOWS".
J. rfCi~n~pltf.
Phys.,
49,357-393.
12. I-lartenlA. and Oshcr, S. (1987)"Uniformly High-Order Accurate Non-0scill;ttory Schemes", SIAM J.
<fNuv~her.A~~rrl~xis,
24 (Z), 231-303.
13. Boris.J. P.;ind Book. D. L.(1973)"Flux CorreclcdTransport I: SHASTA. A Fluid Transport Aleorilhm
-
That Works", J. ~,jComp~rr.
P/I.IX. l I,38-69.
14. Oran. E. S. and Boris.J. P.(1987)Nu~~~ericolSi~~~rrlorior~ojRem:fiee
Fkm',Elscvier Science PublishingCo.
Inc.
15. Ergun. S. (1952) "Fluid Flow Through Packed Columns, Chemical Engineering Progress", 48,89.
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17. Lohner, R.. Morgan, K., Pcroire. J. and Vahdati, M. (1987) "Finite Elcment Flux-Corrected Transport
(FEM-FCT)forEuler and Navicr-Stokes Equations", In!. J.Jor N~IIII~T.
Mefkorlsir~
Flui~is,7,1093-1 109.
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Analysis of combustion processes in a gun ib

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