Abstract
Full Navier-Stokes calculations on the F/A-18A High Alpha Research Vehicle inlet at 30 deg angle of attack, 0 deg yaw, and a freestream Mach number of 0.2, have been obtained in this study using an algebraic turbulence model with two grids (original and revised). In addition, a limited set of results were obtained using a thinlayer Navier-Stokes (TLNS) code with the revised grid. The limitedness of the results was due to the inadequacy of the grid to meet the requirements of the TLNS code. Results obtained with the original grid were used to determine where further grid refinements and additional geometry were needed. The calculations are compared to a limited amount of available experimental data. The predicted forebody/fuselage surface static pressures compared well with data for all solutions. The predicted trajectory of the vortex generated under the leadingedge extension was different for each solution. These discrepancies are attributed to differences in the grid resolution, turbulence modeling, artificial dissipation, and differencing schemes. All solutions predict that this vortex is ingested by the inlet. The predicted 40-probe rake inlet total pressure recoveries are lower than data and the distortions are higher than data. The results obtained with the revised grid were significantly improved from the original grid results.
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