Post on 17-Mar-2021
Three-dimensional high order large-scale numerical
investigation on the air explosion
Cheng Wanga, JianXu Dinga, Chi-Wang Shub,∗, Tao Lia
aState Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing
100081, ChinabDivision of Applied Mathematics, Brown University, Providence, RI 02912, USA
Abstract
Based on the double shockwave approximation procedure and combining the real ghost fluid
method (RGFM) with the level-set method, a local Riemann problem for strongly nonlinear
equations of state such as the JWL equation of state is constructed, which has suppressed
successfully the numerical oscillation caused by high-density ratio and high-pressure ratio
across the interface between the explosion products and the air. A fifth order finite difference
weighted essentially non-oscillatory (WENO) scheme and a third order TVD Runge-Kutta
method are utilized for spatial discretization and time advance, respectively. A fully enclosed
type MPI-based parallel methodology for the RGFM procedure on a uniform structured mesh
is presented to realize the parallelization of the three-dimensional RGFM-based code for the
air explosion. The overall process of the three-dimensional air explosions of both TNT and
aluminized explosives has been successfully simulated. The overpressure at different locations
of the three-dimensional air explosions for both explosives mentioned above is monitored and
analyzed for revealing the influence of the aluminum powder combustion on the overpressure
of the explosion wave. The numerical results indicate that, due to the aluminum powder
afterburning, the attenuation of the explosion wave formed by the aluminized explosives is
slower than that caused by TNT.
Keywords: Air explosion, WENO scheme, RGFM, local Riemann solver, parallelcomputation
∗Corresponding author: shu@dam.brown.edu
Preprint submitted to Elsevier November 4, 2015
1. Introduction
Air explosion is a typical multi-medium problem, in which the explosive flow field usually
consists of many media such as detonation products and air. It is obvious that the sharp
medium interface with high-density ratio and high-pressure ratio separates the detonation
products from the air. In the numerical simulation of the air explosion problem, because
of the abrupt change of density and pressure close to the interface, unphysical numerical
oscillations may easily appear in the neighborhood of the interface. Meanwhile, with the
continuous upgrade of the explosives, density ratio and pressure ratio increase constantly and
significantly. Therefore, tracking and treating the strong nonlinear discontinuous interface
in the air explosion have received considerable attention.
Many interface tracking techniques have been discussed over the past few decades. The
marker-and-cell (MAC) method proposed by Harlow and Welch [1] has often been used to
track the interface movement and the flow field evolution. However, the maintenance of
a sharp interface among multi-media is difficult. Hirt and Nichols [2] presented another
interface tracking algorithm known as the volume-of-fluid (VOF) method without tracking
the motion of the multi-medium interface, in which, as time increases, the volume of each
medium in each cell is changing continuously and the new interface is reconstructed from the
values of the volumes at the current time level. The main drawback of the VOF method is
that, for deciding the orientation of the multi-medium interface, massive non-local data must
be taken into consideration. To overcome such drawbacks of the VOF method, the moment of
fluid (MOF) method introduced by Ahn and Shashkov [3] and by Dyadechko and Shashkov
[4] with second order accuracy employed not only volume fractions but also the position
of the centroids of each medium, which allows the MOF method to utilize the cell where
reconstruction is performed. The well-known particle-in-cell (PIC) algorithm by Amsden [5]
is a Lagrangian description of flows in which particles are explicitly associated with different
media and thus the interface can be tracked easily. The principal drawbacks are a large
numerical diffusion and a numerical noise, due to the momentum transfer between grids and
particles and the employment of finite particle numbers. The level set method developed
2
by Osher and Sethian [6] is a simple and versatile method for tracking the evolution of a
locomotive interface. The level-set method [7, 8, 9] uses a Hamilton-Jacobi equation to
describe the moving interface, which is tracked as the zero level set of a continuous function
mimicking the signed distance function instead of an explicit function at the new time level.
Thus, cases with complex interfaces, such as crisscross, torsion and separation, etc., can be
easily handled by the level-set method.
Fedkiw et al. [10] presented the original ghost fluid method (OGFM), which can address
excellently the interaction between a weak shock wave and an interface. To further improve
the accuracy of the OGFM method, Liu et al. [11] discussed the modified ghost fluid method
(MGFM) procedure, which performed better than the OGFM due to a local Riemann solver,
where the status of the ghost fluid across the interface for each phase was defined by the
predicted interfacial status by this Riemann solver. The accuracy of the MGFM for the gas-
gas Riemann problem performed by Liu et al. in [12] showed that, compared with the exact
solution of a Riemann problem, the MGFM solution could reach second order accuracy
near the multi-medium interface. The key point of the real ghost fluid method (RGFM)
procedure, presented by Wang et al. [13] was that, according to the status of media across
the interface, a local Riemann problem was constructed at first and the interfacial status
obtained was then used to redefine the flow states for not only the real fluid grid points
next to the interface but also to the ghost fluid grid points, by which smaller errors were
introduced in the RGFM procedure in comparison to the MGFM procedure.
Since the OGFM, MGFM and RGFM were introduced, an increasing number of numerical
simulations combining these methods for multi-medium flows can be found in the literature.
However, most of these previous simulations with GFM-based procedures use the simple and
linear equations of state for describing the media of interest such as explosion products and
air in the air explosion, while the complex equations of state such as JWL have seldomly
been used. Meanwhile, numerical simulations based on the RGFM procedure by splitting
a multi-medium problem into single medium flows, usually require large parallel computer
resources. In general, serial computation cannot meet the requirements of multi-dimensional
large-scale engineering applications.
3
In this paper, based on a double shockwave approximation procedure, we first present
in detail a technique to construct and solve the local Riemann problem with the complex
equations of state such as the JWL equation of state used in the air explosion simulations.
Our numerical simulation demonstrates that this technique effectively eliminates unphysical
oscillations which often occur at the multi-medium interface in the explosive flow field. Com-
bining the RGFM method, formally transforming the multi-medium flow field into single flow
fields with an enclosed type parallelization module, the mechanisms of the three-dimensional
air explosion are studied by using the fifth order finite difference weighted essentially non-
oscillatory (WENO) scheme on a uniform structured mesh.
2. Governing equations
The governing equations in a conservative form without considering the viscous and
thermal diffusion effects for describing a three-dimensional air explosion can be written as
∂U
∂t+
∂F (U)
∂x+
∂G(U)
∂y+
∂H(U)
∂z= 0
U = (ρ, ρu, ρv, ρw, ρE)T
F (U) = (ρu, ρu2 + p, ρuv, ρuw, (ρE + p)u)T
G(U) = (ρv, ρuv, ρv2 + p, ρvw, (ρE + p)v)T
H(U) = (ρw, ρuw, ρvw, ρw2 + p, (ρE + p)w)T
(1)
where ρ and p denote the density and pressure, respectively. u, v and w are the velocity
components in the x ,y and z directions in the Euler coordinates, and E is the total energy,
generally consisting of internal energy and kinetic energy, is given as
E =(u2 + v2 + w2)
2+ e (2)
where e is the internal energy per unit mass.
For the aluminized explosive, the Miller model [14] describing the combustion and heat
release process of the aluminum powder can be used to describe the reaction process. By
coupling the above three-dimensional Euler equations with the Miller model, the complete
process of the air explosion for the aluminized explosive can be captured numerically. The
4
Tab. 1: JWL EOS parameters for the explosion products of the TNT charge.
ρ0(kg/m3) A(MPa) B(MPa) R1 R2 ω
1630.0 373800.0 3747.0 4.15 0.9 0.35
Miller model given in [14] and used in this paper is
∂λ
∂t=
1
4(1 − λ)
12 p
16 (3)
where λ is the chemical reaction process variable characterizing the aluminum powder reac-
tion degree. The reaction process parameters λ = 0 and λ = 1 are defined as the initially
unreacted and completely burned states, respectively.
To close the above governing equations, the respective equations of state for the air and
for the explosion products of TNT and aluminized explosive must be introduced. The ideal
gaseous equation of state for the air medium can be presented as
p = (γ − 1)ρe (4)
where e is the specific internal energy and γ = 1.4 for air is the gaseous constant which
depends on the particular gas of interest.
The explosion products of the TNT charge are usually described by the JWL equation
of state [15], which can be expressed in the following form
p = A(1 −ωρ
R1ρ0)e−
R1ρ0ρ + B(1 −
ωρ
R2ρ0)e−
R2ρ0ρ + ωρe (5)
where ρ, p and e denote the density, pressure and the specific internal energy in unit mass,
respectively. The parameters A, B, R1, R2, ω and ρ0 are material constants of the detonation
products, which are specifically shown in Table 1.
The equation of state of the detonation product of aluminized explosives should be able to
establish the essential relationship among pressure, density, internal energy and the reaction
process variable. The JWL-Miller equation of state [14] for describing the detonation product
of aluminized explosives are adopted as
p = A(1 −ωρ
R1ρ0)e−
R1ρ0ρ + B(1 −
ωρ
R2ρ0)e−
R2ρ0ρ +
ωρ(E + λQ)
ρ0
(6)
5
Tab. 2: JWL-Miller EOS parameters for the explosion products of aluminized explosives.
A(MPa) B(MPa) R1 R2 ω ρ0(kg/m3) Q(MPa)
695130.0 3130.0 5.4 1.4 0.4 1880 11000
where ρ, p and E denote the density, pressure and the energy content of the explosive which
keeps the CJ condition, respectively. The constant Q is defined as the afterburning energy
release after the CJ plane. The parameters A, B, R1, R2, ω and ρ0 are material constants
of the detonation products, which can be found in Table 2.
The semi-discrete approximation of equation (1) is given by
(∂U
∂t)i,j,k = −
1
∆x(Fi+ 1
2,j,k − Fi− 1
2,j,k) −
1
∆y(Gi,j+ 1
2,k − Gi,j− 1
2,k)
−1
∆z(Hi,j,k+ 1
2− Hi,j,k− 1
2)
(7)
where Fi+ 12,j,k ,Gi,j+ 1
2,k and Hi,j,k+ 1
2present the numerical fluxes, which are obtained by a fifth
order finite difference WENO scheme with the Lax-Friedrichs splitting [16]. A third order
TVD Runge-Kutta scheme [17] is used to integrate the system of the ordinary differential
equations (7) in time. The parallel adaptive code to solve three-dimensional detonation
problems is developed in [18].
3. The local Riemann solver for the air explosion
The level set technique provides an efficient method to describe multi-medium flows and
to track the interfaces, and is used in this paper. Besides the high order solution of the
Hamilton-Jacobi type equations with the methods presented in the literature [19, 20], the
reinitialization of the level set is a necessary step in the level set method to keep the level set
function close to the signed distance function and hence to maintain efficiency of the overall
solution method [21, 22, 23, 24]. After confirming the specific locations of the interface
between the explosion products and the air by advancing the implicit level-set function, the
RGFM-based multi-medium interface treatment should be utilized to change a multi-medium
problem into two single medium problems. In the RGFM method, a local Riemann problem
is constructed first at the interface and then solved. The predicted interface values obtained
6
by the Riemann solver are assigned to the real fluid nodes next to the interface in the real
fluid. Then, a normal constant extrapolation by solving the extension equation [25] is used
to acquire the values of the three ghost fluid nodes required for a fifth order WENO scheme
used for each pure medium.
Next, the solution to a local Riemann problem in the air explosion will be presented in
detail. Taking the one dimensional case as an example, with the help of the mass conservation
equation and the momentum conservation equation, the expression bridging the velocity and
pressure of the interface can be obtained as
u∗ = F1(p∗) = uL −
√(p∗ − pL)(
1
ρL−
1
ρ∗L) (8)
u∗ = F2(p∗) = uR +
√(p∗ − pR)(
1
ρR−
1
ρ∗R) (9)
here ρ∗L and ρ∗R are the densities on both sides of the interface, which are unknown quantities
for the time being and also need to be solved.
The nonlinear function relationship with respect to the interfacial pressure is obtained
by the above two equations, which can be easily written as
F (p∗) = F1(p∗) − F2(p∗) = 0 (10)
Combining the energy conservation equation with the equations of state, the implicit
function in regard to ρ∗L, ρ∗R and p∗ can be deduced as
eL(pL, ρL) − e∗L(p∗, ρ∗L) −1
2(pL + p∗)
ρL − ρ∗L
ρLρ∗L
= 0 (11)
e∗R(p∗, ρ∗R) − eR(pR, ρR) −1
2(p∗ + pR)
ρ∗R − ρR
ρ∗RρR= 0 (12)
For the local Riemann problem comprising of the JWL equation of state and gas equation
of state, the process of solving equation (10) by a Newton iterative method is described below.
It is first supposed that, for the one dimensional Riemann problem, the gaseous explosion
products are located at the left side of the interface and the air is on the right side. Obviously,
(10), (11) and (12) are now a system of nonlinear equations consisting of interfacial pressure
and densities on both sides of the interface as unknown variables. Thus the classical Newton
7
iterative method could be used to solve it:
p∗(n+1) = p
∗(n) −F1(p∗(n)) − F2(p∗(n))
F′
1(p∗(n)) − F′
2(p∗(n))(13)
The initial guess of p∗ is necessary for the Newton iteration, and should be selected
properly. Then the JWL equation of state is plugged into equation (11), and the following
implicit relation can be given
(pL − A(1 −ωρL
R1ρ0
)e−
R1ρ0ρL − B(1 −
ωρL
R2ρ0
)e−
R2ρ0ρL )ρ∗L
− (p∗ − A(1 −ωρ∗L
R1ρ0)e
−R1ρ0ρ∗L − B(1 −
ωρ∗L
R2ρ0)e
−R2ρ0ρ∗L )ρL −
1
2ω(pL + p∗)(ρL − ρ∗L) = 0
(14)
With an appropriate initial guess p∗, equation (14) becomes a nonlinear equation for the
dependent variable ρ∗L, which also needs to be solved using the Newton iterative method.
During the iterative process, the derivative of the equation (14) with respect to the density
can be written as
∂f
∂ρ∗L=pL + ρL(
Ae−
R1ρ0ρ∗L (R1ρ0 − ωρ∗L)
ρ2∗L
+Be
−R2ρ0ρ∗L (R2ρ0 − ωρ∗L)
ρ2∗L
)
− ρL(Aωe
−R1ρ0ρ∗L
R1ρ0
+Bωe
−R2ρ0ρ∗L
R2ρ0
) + ω(pL
2+
p∗2
)
−Ae
−R1ρ0
ρL (R1ρ0 − ωρL)
R1ρ0
−Be
−R2ρ0
ρL (R2ρ0 − ωρL)
R2ρ0
(15)
Similarly, for the ideal gaseous equation of state, we have
p∗γ − 1
−pRρ∗R
(γ − 1)ρR−
1
2(p∗ + pR)
ρ∗R − ρR
ρR= 0 (16)
The derivative of equation (16) with respect to the density can be given easily as
∂f
∂ρ∗R= −
pR + p∗2ρR
−pR
ρR(γ − 1)(17)
Now we substitute both the pressure p∗ and the density ρ∗L obtained by the iterative
method into equation (8) to produce the expression F1(p∗). In the same way, substitution of
the given p∗ and the iteration density ρ∗R into equation (9) yields F2(p∗). Apparently, the
derivatives of the functions F1(p∗) and F2(p∗) with respect to the interface pressure p∗ are
dF1(p∗)
dp∗= −
√
−
1ρ∗L
− 1ρL
p∗ − pL−
ρ′
∗L(p∗−pL)
ρ2∗L
+ 1ρ∗L
−1
ρL
p∗−pL
2
√−
1ρ∗L
−1
ρL
p∗−pL
(18)
8
dF2(p∗)
dp∗=
√
−
1ρ∗R
− 1ρR
p∗ − pR
+
ρ′
∗R(p∗−pR)
ρ2∗R
+ 1ρ∗R
−1
ρR
p∗−pR
2
√−
1ρ∗R
−1
ρR
p∗−pR
(19)
By a direct calculation of the derivatives of the density ρ∗L and ρ∗R at both sides of the
interface with respect to the interface pressure, we arrive at the desired results as follows
dρ∗L
dp∗=
ρL + ω(ρL−ρ∗L)2
pL + ρL(Ae−
R1ρ0ρ∗L (R1ρ0−ωρ∗L)
ρ2∗L
+ Be−
R2ρ0ρ∗L (R2ρ0−ωρ∗L)
ρ2∗L
− Aωe−
R1ρ0ρ∗L
R1ρ0− Bωe
−R2ρ0ρ∗L
R2ρ0)
+ ω(pL
2+
p∗2
) −Ae
−R1ρ0
ρL (R1ρ0 − ωρL)
R1ρ0
−Be
−R2ρ0
ρL (R2ρ0 − ωρL)
R2ρ0
(20)
dρ∗R
dp∗= −
1γ−1
− 12(ρ∗R
ρR− 1)
pR+p∗2ρR
+ pR
ρR(γ−1)
(21)
By substituting F1(p∗), F2(p∗), F′
1(p∗), F′
2(p∗) obtained above into equation (13), the new
pressure p∗(n+1) is obtained, which will be used as the starting value for the next iteration.
If the difference |p∗(n+1) − p∗(n)| is smaller than a threshold, the Newton iteration will be
stopped, and the final result p∗(n+1) is recorded as the pressure p∗. Then, the velocity and
the two values of density can be obtained by simultaneously solving (8), (11) and (12), and
the solution to the local Riemann problem in the air explosion is completed.
4. Parallelization for the RGFM procedure
For parallel implementation, the computational domain should first be divided into many
small subdomains. That is to say, each processor is only responsible for computing the
corresponding subdomain, as shown in Fig. 1. In this section we sometimes use the two-
dimensional case for illustration.
When calculating the spatial derivatives at any grid point, it is necessary to obtain the
values of its adjacent nodes for interpolation. The template for the fifth order WENO scheme
requires seven grid points, which is obviously wider than the traditional lower order schemes.
For such grid points close to the border of any processor, the corresponding information
required for interpolation may be located in other adjacent processors, as shown in Fig.
2. It can be seen from Fig. 2 that the computation of several columns of grid points
located at the right side of the yellow middle processor would need to use information in
9
Fig. 1: Computational domain divided equally into subdomains for parallel implementation.
the right adjacent processor. Therefore, the information of the adjacent processors must be
transmitted into the current processor for parallel computation.
Fig. 2: Data communication required by a finite difference WENO scheme.
For an ordinary finite difference scheme, it generally only requires to communicate data
of the current processor with its adjacent processors in the orthogonal directions. That is
to say, information in the processors in the diagonal directions are not needed. For the
numerical simulations of the air explosion based on the RGFM combined with the WENO
scheme, however, the situation may be different. If the interface formed by the explosion
products and the air is very close to a corner of any subdomain belonging to a computational
processor, information such as pressure and density at some grid points of the adjacent
diagonal processor to that corner may be needed in the construction of the local Riemann
solver, as shown in Fig. 3. Considering such special requirements for the RGFM method to
10
Fig. 3: Possible data communication required by RGFM.
data communication, a fully enclosed type data communication mode is presented, in which
the enclosed communication ghost layers with a width of several grid points are created on
the periphery of the computational subdomain for any processor. Through the real-time data
communication based on the presented parallel method, it can ensure that, similar to the
serial run environment, any subdomain can be computed efficiently. In a three-dimensional
flow field, for a processor not located at the border of the computational domain, there are
26 adjacent processors. Therefore, 26 “send” buffers corresponding to 26 “receive” buffers
are established. Fig. 4 shows the computational subdomain of an individual processor.
The cubic area surrounded by the light color lines in the middle is an actual computational
subdomain using the WENO scheme for the current processor. Others are not only the ghost
layers but also the 26 “receive” buffers. It should be noted that, without loss of generality,
the corresponding 26 “send” buffers are not illustrated in Fig. 4.
Fig. 4: An enclosed type data communication style for an individual processor.
11
Table 3 shows the number of all the “send” buffers and their processors corresponding to
all the “receive” buffers for the n-th subdomain, and the number of all the “receive” buffers
and their processors corresponding to all the “send” buffers for the n-th subdomain. It is
noted that notations x and y refer to the respective numbers of processors in the horizontal
and vertical directions.
Tab. 3: Communication mode for the n-th receive (send) processor.
Processor number Receive (send) Send (receive) Processor numberof receive (send) buffer buffer number buffer number of send (receive) buffer
n 1 8 n-xy-x-1n 2 7 n-xy-x+1n 3 6 n-xy+x-1n 4 5 n-xy+x+1n 5 4 n+xy-x-1n 6 3 n+xy-x+1n 7 2 n+xy+x-1n 8 1 n+xy+x+1n 9 12 n-xy-xn 10 11 n-xy+xn 11 10 n+xy-xn 12 9 n+xy+xn 13 16 n-xy-1n 14 15 n-xy+1n 15 14 n+xy-1n 16 13 n+xy+1n 17 20 n-x-1n 18 19 n-x+1n 19 18 n+x-1n 20 17 n+x+1n 21 22 n-1n 22 21 n+1n 23 24 n-xn 24 23 n+xn 25 26 n-xyn 26 25 n+xy
The classical fifth order WENO scheme used in this paper needs three layers of ghost
points for the current computational processor. As for the RGFM method, the grid points
beyond the three ghost layers are definitely not needed when constructing the local Riemann
12
Problem. Therefore, the enclosed type MPI-based parallel procedure containing three ghost
layers of grid points are employed in all the following numerical examples.
5. Numerical investigation on the three-dimensional air explosion
5.1. Numerical investigation on the air explosion for the TNT charge
In this subsection, simulations of the air explosion for the TNT charge are performed uti-
lizing a parallel high order code described previously. The explosion products are described
by the JWL EOS, and its parameters can be found in Table 1. The initial pressure of the
explosion products achieved in this subsection is 8.6 GPa. The computational model can be
seen in Fig. 5 for the air explosion.
Fig. 5: The parallel computational model for the air explosion.
Before performing a series of numerical simulations, the convergence of the computational
code with increasing resolution for the air explosion is validated for this study. The com-
putational domain with the TNT charge radius of 0.3m is 7.8m×7.8m×7.8m. To accelerate
the speed of computations, 64 processors are employed to compute this problem. When the
difference of pressure between two mesh sizes monitored at the location (5.6m, 3.9m, 3.9m)
is small enough, grid convergence is declared. Fig. 6 illustrates the evolution of the explosion
overpressure for three different mesh sizes (0.03m, 0.02m and 0.01m). It is observed clearly
from Fig. 6 that grid convergence can be attained with a mesh size of 0.02m.
In order to demonstrate and validate the stability and reliability of the numerical results,
the explosion wave overpressure values obtained at different locations are compared with the
13
Fig. 6: The convergence of mesh refinements.
empirical formula in Henrych [26]. 64 processors are employed to compute this problem with
up to 59.78 million grid points. The size of a uniform cubic mesh is 0.02m×0.02m×0.02m,
while the total physical domain with the TNT charge radius of 0.21m is also 7.8m×7.8m×7.8m.
The comparison is shown in Fig. 7. It is clear that, except for the region of the near field (in
which the proportional distance is less than 0.348 m/kg1/3), the explosion wave overpressure
obtained by the numerical simulation is in good agreement with the empirical formula, with
a relative error less than 8.3 percent. As a result, the material interface treatment combining
level-set technique with the RGFM method based on a shock-shock Riemann solver can be
applied successfully to the numerical simulations of the air explosion. At the same time, the
comparison also shows that neglecting the details of the explosion process has little effect
on the results of the numerical calculation by simplifying the explosive products into a high
temperature and high pressure gas.
The numerical results reveal that the essential physics of the expansion of the interface
is the movement of the contact discontinuity for a local Riemann problem at the interface,
and the pressure, normal speed and density close to the interface determine the evolution of
the interface. Thus, solving the local Riemann problem is an effective way to quantitatively
reveal the evolution mechanism of the air explosion. Solving the local Riemann problem can
obtain accurately flow characteristics near the interface and inside the flow field. Therefore,
the unique advantages based on the RGFM procedure and the local Riemann solver make
14
Fig. 7: The explosion wave overpressure peaks obtained by both the numerical simulationand the empirical formula.
the procedure ideal for simulating the air explosion.
The computational results at several temporal moments are shown in Figures 8 to 10.
In order to observe directly the distribution of the physical variables such as pressure and
density inside the three-dimensional internal explosion field, the results in only part of the
computational domain are shown. It can be seen from Figures 8 to 10 that the contours of
density and pressure are very symmetrical and nonphysical oscillations do not appear. The
distribution of density and pressure in the air explosion field can also be revealed clearly.
Fig. 8: The numerical results at 0.50ms: (a) Pressure contour; (b) Density contour.
Fig. 11 shows the distribution of pressure and density for the spherical explosion field
along the central axis at 0.772 ms. It is obvious that there are two density peaks in the
typical explosion field. The first peak is inside the explosion products close to the interface
15
Fig. 9: The numerical results at 1.01ms: (a) Pressure contour; (b) Density contour.
Fig. 10: The numerical results at 1.71ms: (a) Pressure contour; (b) Density contour.
16
of the material, while the other one appears in the explosion wave front in the air. The curve
describing the evolution of the pressure has only one peak, and the transition of pressure
is continuous at the interface between the explosion products and the air. It can also be
found that, in the rapid expansion process of the air caused by the explosion products with
an extremely high temperature and pressure, the rarefaction wave propagates back into the
explosion products and converges to the center of the spherical explosion products, which
dramatically attenuates the pressure in the zones swept by the rarefaction wave. At 0.772
ms, the density distributes from 0.5 kg/m3 to 1.0 kg/m3, which is slightly lower than that
under the ambient temperature and pressure; the pressure is less than 0.1 MPa, which is also
below the normal atmospheric pressure. However, a narrow banded zone with relatively high
pressure and density is located inside the explosion products and close to the propagating
interface. At 0.772 ms, the maximum pressure and density can reach up to 0.86 MPa and 3.3
kg/m3, respectively, which are much higher than the atmospheric ones under the ambient
temperature and pressure.
Fig. 11: The distributions of pressure and density along the center axis at 0.772ms: (a)Pressure curve; (b) Density curve.
5.2. Numerical investigation on the air explosion of aluminized explosives
In this subsection simulations of the air explosion for aluminized explosives with the
radius of 0.21m are performed. The JWL-Miller EOS is used to describe the explosion
products, and Table 2 gives all the parameters used. For simplicity, the ignition and reaction
process of the aluminized explosives are again omitted in the air explosion. The initial
pressure used in this subsection of explosion products is 6.26 GPa. The numerical results
17
are again obtained with 64 processors and the total number of grid points is 59.78 million.
The mesh size is 0.02m×0.02m×0.02m. The computational domain is 7.8m×7.8m×7.8m.
Fig. 12: The numerical results for the aluminized explosive: (a) Pressure contour; (b) Densitycontour; (c) Level-set contour; (d) Aluminum powder reaction fraction contour.
Fig. 12 shows the contours of the computational results for part of the computational
domain for the aluminized explosives. Table 4 shows the evolution of the explosion wave
overpressure peak for the aluminized explosive with the change of the proportional distance.
Fig. 13 compares explosion wave overpressure peaks of the TNT charge with that of the
aluminized explosives with the variation of proportional distance. It can be seen from Fig. 13
that the explosion wave overpressure peaks caused by the aluminized explosive are obviously
lower than that of TNT in the near field. However, because the secondary energy release
process caused by the aluminum powder afterburning can continuously supplement energy,
the energy loss in the propagating process of the explosion wave is replenished to some
18
Tab. 4: The explosion wave overpressure peaks for the aluminized explosive at differentproportional distances.
Proportional 0.182 0.249 0.332 0.415 0.497 0.580 0.663 0.746 0.829distance(m/kg1/3)
Overpressure 8.09 6.85 5.31 4.10 3.22 2.52 1.97 1.55 1.25peak(MPa)
extent. Therefore, the explosion wave attenuation of the aluminized explosive is relatively
slow, and, its overpressure will gradually catch up with and then surpass that formed by the
TNT as the explosion wave spreads forward to the far field.
Fig. 13: The comparison of the explosion wave overpressure peaks between TNT and alu-minized explosives in the air explosion.
6. Concluding remarks
Combining the RGFM multi-medium interface treatment method with a fifth order fi-
nite difference WENO scheme, and based on a Riemann solver presented for the nonlinear
equations of state and the MPI-based enclose type parallel mode, the large-scale air explo-
sion parallel code is developed to successfully simulate the three-dimensional air explosion
processes for the TNT charge and aluminized explosives. First of all, the air explosions of
the three-dimensional spherical TNT are carried out numerically, and then the distribution
19
of the physical quantities such as density and pressure are obtained in the explosive flow
field. The validation of the code based on the RGFM for simulating air explosion is given
through comparing the explosion wave overpressures of the numerical results with those of
the Henrych empirical formula [26]. The errors are less than 8.3 percent except for the region
of the near field close to the interface in the air. At the same time, it is also demonstrated
that, neglecting the reaction process in the air explosion, as is done in this paper to simply
the computation, has little impact on the numerical results of the far field explosion over-
pressure. Next the air explosion of the spherical aluminized explosive is simulated to obtain
the pressure and density distribution in the explosion field. The overpressure peaks of the
TNT charge and the aluminized explosive are compared with the variation of proportional
distance. This comparison shows that the subsequent aluminum powder afterburning gives
rise to secondary energy release and forces the relatively slow attenuation of the explosion
wave overpressure peaks of the aluminized explosive.
Acknowledgments
The research of Wang, Ding and Li is supported by the National Natural Science Founda-
tion of China under grants 11325209 and 11221202, the Specialized Research Foundation for
the Doctoral Program of Higher Education of China under grant 20121101110004, and the
Beijing Natural Science Foundation under grant 8132034. The research of Shu is supported
by ARO grant W911NF-15-1-0226 and NSF grant DMS-1418750.
References
[1] F.H. Harlow and J.E. Welch. Numerical calculation of time dependent viscous incom-
pressible flow of fluid with free surface. Phys. Fluids, 1965, 8:2182-2189.
[2] C.W. Hirt and B.D. Nichols. Volume of fluid (VOF) method for the dynamics of free
boundaries. J. Comput. Phys., 1981, 39:201-225.
[3] H. Ahn and M. Shashkov. Multi-material interface reconstruction on generalized poly-
hedral meshes. J. Comput. Phys., 2007, 226:2096-2132.
20
[4] V. Dyadechko and M. Shashkov. Reconstruction of multi-material interfaces from mo-
ment data. J. Comput. Phys., 2008, 227:5361-5384.
[5] A. Amsden. The particle-in cell method for the calculations of the dynamics of com-
pressible fluids. Los Alamos Scientific Laboratory Report, 1966, LA-3466.
[6] S. Osher and J.A. Sethian. Fronts propagating with curvature dependent speed: algo-
rithms based on Hamilton-Jacobi formulations. J. Comput. Phys., 1988, 79:12-49.
[7] S. Osher and R. Fedkiw. Level Set Methods and Dynamic Implicit Surfaces. Springer,
New York, 2003.
[8] J.A. Sethian. Theory, algorithms, and applications of level set methods for propagating
interfaces. Acta Numer., 1996, 5:309-395.
[9] D. Adalsteinsson and J.A. Sethian. The fast construction of extension velocities in level
set methods. J. Comput. Phys., 1999, 148:2-22.
[10] R. Fedkiw, T. Aslam, B. Merriman and S. Osher. A non-oscillatory Eulerian approach
to interfaces in multimaterial flows (the ghost fluid method). J. Comput. Phys., 1999,
152:457-492.
[11] T.G. Liu, B.C. Khoo and K.S. Yeo. Ghost fluid method for strong shock impacting on
material interface. J. Comput. Phys., 2003, 190:651-681.
[12] T.G. Liu and B.C. Khoo. The accuracy of the modified ghost fluid method for gas-gas
Riemann problem. Appl. Numer. Math., 2007, 57:721-733.
[13] C.W. Wang, T.G. Liu and B.C. Khoo. A real ghost fluid method for the simulation of
multimedium compressible flow. SIAM. J. Sci. Comput., 2006, 28:278-302.
[14] P.J. Miller. A reactive flow model with coupled reaction kinetics for detonation and
combustion in non-ideal explosives. Mat. Res. Soc. Symp. Proc., 1996, 418:413-420.
[15] E.L. Lee, H.C. Hornig and J.W. Kury. Adiabatic expansion of high explosive detonation
products. UCRL Report, 1968, UCRL-50422.
21
[16] G.S. Jiang and C.-W. Shu. Efficient implementation of weighted ENO schemes. J. Com-
put. Phys., 1996, 126:202-228.
[17] C.-W. Shu and S. Osher. Efficient implementation of essentially non-oscillatory shock-
capturing schemes. J. Comput. Phys., 1988, 77:439-471.
[18] C. Wang, X.Z. Dong and C.-W. Shu. Parallel adaptive mesh refinement method based
on WENO finite difference scheme for the simulation of multi-dimensional detonation.
J. Comput. Phys., 2015, 298:161-175.
[19] G.-S. Jiang and D. Peng. Weighted ENO schemes for Hamilton-Jacobi equations. SIAM
J. Sci. Comput., 2000, 21:2126-2143.
[20] R. Nourgaliev and T. Theofanous. High-fidelity interface tracking in compressible flows:
unlimited anchored adaptive level set. J. Comput. Phys., 2007, 224:836-866.
[21] M. Sussman, P. Smereka and S. Osher. A level set approach for computing solutions to
incompressible two-phase flow. J. Comput. Phys., 1994, 114:146-159.
[22] P.A. Gremaud, C.M. Kuster and Z.L. Li. A study of numerical methods for the level
set approach. Appl. Numer. Math., 2007, 57:837-846.
[23] D. Hartmann, M. Meinke and W. Schroder. Differential equation based constrained
reinitialization for level set methods. J. Comput. Phys., 2008, 227:6821-6845.
[24] D. Hartmann, M. Meinke and W. Schroder. The constrained reinitialization equation
for level set methods. J. Comput. Phys., 2010, 229:1514-1535.
[25] T.D. Aslam. A partial differential equation approach to multidimensional extrapolation.
J. Comput. Phys., 2003, 193:349-355.
[26] J. Henrych. The Dynamics of Explosion and Its Use. Elsevier Scientific Publishing Com-
pany, Amsterdam and New York, 1979, 178-181.
22