Inviscid Supersonic Flow Over F-16 Aircraft Simulation

$210.00 Student Discount

In this project, Inviscid Supersonic Flow Over F-16 Aircraft has been simulated, and the results of this simulation have been investigated.

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Inviscid Supersonic Flow Over F-16 Aircraft, CFD Simulation Ansys Fluent Training

In this project, supersonic flow over an F-16 aircraft considering inviscid fluid was simulated in Ansys Fluent software, and then the results were investigated. Supersonic speed is the speed of an object that exceeds the speed of sound. It is estimated to be around 343 m/s in the dry air at a temperature of 20 C. In this simulation, the F-16 aircraft experiences 400m/s speed, so the Mach number is 1.16, and the working fluid is assumed to be inviscid, so there would be no shear stress.

Geometry & Mesh

The 3D geometry was imported and generated in Design Modeler software. An F-16 aircraft model is imported and placed at the middle of an enclosure. In addition, an unstructured mesh grid was carried out using Ansys meshing software, and overall, 979273 elements were generated.


Inviscid Supersonic Flow CFD Simulation

Several assumptions have been considered to simulate supersonic flow over F-16 aircraft, including:

  • The simulation is Steady, so the conditions don’t change with time.
  • The pressure-based solver type was used within the ideal-gas behavior of air density.
  • An inviscid viscous model was utilized.
  • Gravitational acceleration effects were neglected.

The following table represents a summary of the solution:

Viscous Inviscid
  Energy on
Fluid Definition method Fluent database
Material name Air
  Density Ideal-gas
Cell zone condition
Material name Air
Boundary condition
Inlet Type Velocity inlet
Velocity magnitude 400m/s
Outlet Type Pressure-oulet
Gauge pressure 0
Wall-solid Type Pressure-far-field
Mach number 1.16
Solver configuration
Pressure-velocity coupling Scheme Coupled
Spatial Discretization Gradient Least squares cell-based
Pressure Second-order
Momentum Second-order upwind
Initialization Initialization methods Standard Initialization
Run calculation Number of iterations 600


Although air is considered an incompressible fluid in most cases when the speed of fluid increases, there should be an assumption of compressibility; this assumption is specified by a dimensionless factor called Mach number, which represents fluid velocity to the velocity of sound in a defined condition. In this simulation, the inlet velocity is 400m/s, so the Mach number is 1.16 and could be counted as supersonic flow. A pressure-based solver was used along with the ideal-gas behavior of fluid and coupled pressure-velocity coupling scheme instead of using density-based solver and its convergence problems.

The contours of the simulation clearly show the symmetric distribution of pressure and velocity field around the aircraft. The pressure gets to its highest values below the wings and this pressure gradient causes lift force acts on aircraft. Moreover, there is a strong correlation between pressure, density, and temperature. Note that the fluid is assumed to be inviscid, and as a result, the Navier-stokes governing equation is simplified to Bernoulli’s equation.


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