530
S. Balasubramanian et al.
Fig. 1 Spherically blunt cone flare
tool. The origin is fixed at the base of the configuration in the symmetry plane. And
the flow direction is −Y-axis. The configuration detail has been reproduced from
reference [1].
2 CFD Simulation Details
The flow domain is created using ANSYS-DesignModeler. The size of the domain is
37D, as shown in Fig. 2. An unstructured grid with the size of 38 lakhs (21 inflation
layer and density box to capture near-body gradients) is generated using ANSYSMeshing tool over the configuration as shown in Figs. 3 and 4. Boundary conditions
applied for the current analysis are inlet, pressure far-field, walls, pressure outlet as
shown in Fig. 2. The flow simulation conditions have been taken from reference [2].
CFD simulations are carried out at Mach numbers ranging from 0.3 to 6 at a 0° angle
of attack. ANSYS-Fluent is the data generation tool and CFD++ software is used for
code-to-code comparison for typical Mach numbers. Finite volume pressure-based
coupled solver with the Spalart-Allmaras turbulence model is used for Mach number
≤1.2. And the density-based solvers are mostly utilized for high-speed compressible
flows. So density-based AUSM flux scheme with a realizable k-ε turbulence model
is used for Mach number >1.2.
S. Balasubramanian et al.
Fig. 1 Spherically blunt cone flare
tool. The origin is fixed at the base of the configuration in the symmetry plane. And
the flow direction is −Y-axis. The configuration detail has been reproduced from
reference [1].
2 CFD Simulation Details
The flow domain is created using ANSYS-DesignModeler. The size of the domain is
37D, as shown in Fig. 2. An unstructured grid with the size of 38 lakhs (21 inflation
layer and density box to capture near-body gradients) is generated using ANSYSMeshing tool over the configuration as shown in Figs. 3 and 4. Boundary conditions
applied for the current analysis are inlet, pressure far-field, walls, pressure outlet as
shown in Fig. 2. The flow simulation conditions have been taken from reference [2].
CFD simulations are carried out at Mach numbers ranging from 0.3 to 6 at a 0° angle
of attack. ANSYS-Fluent is the data generation tool and CFD++ software is used for
code-to-code comparison for typical Mach numbers. Finite volume pressure-based
coupled solver with the Spalart-Allmaras turbulence model is used for Mach number
≤1.2. And the density-based solvers are mostly utilized for high-speed compressible
flows. So density-based AUSM flux scheme with a realizable k-ε turbulence model
is used for Mach number >1.2.