Abstract
The results of a numerical simulation are presented for the steady flow over an F-16A aircraft configuration at a freestream Mach number of 1.2, a Reynolds number of 12.75 x 10, and an angle of attack of 6 deg. The three-dimensional Navier-Stokes equations in mass-averaged variables were integrated numerically using the MacCormack explicit algorithm with an algebraic turbulence model to provide closure of the system of equations. The grid structure, boundary conditions, and solution procedure are discussed in detail for this complex aircraft geometry. The results are then compared to experimental data in terms of surface pressure coefficients, lift coefficient, and drag coefficient with reasonable agreement. Finally, details of the flow are discussed, such as the strake vortex and the wing vortex structures.
Published Version
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