Abstract
This article discusses the flowfield, surface pressure, and integrated forces and moments obtained by solving the Euler equations numerically for a fighter-type forebody with uncambered sharp leading-edge strakes. Predictions are compared with experiment for freestream Mach numbers 1.6, 1.8, and 2.0, and angles of attack from approximately 0-14 deg. Comparison with experimental data showed that the Euler method correctly predicted the leading-edge vortices and embedded shocks which arise at higher angles of attack. However, the vortices due to embedded shock-induced separation, which occurred on the upper forebody aft of the canopy, were not predicted. The effects of crossflow grid density, artificial viscosity, angle of attack, and streamwise station on the computed-flow characteristics were examined. It was found that increasing crossflow grid density resulted in a better resolution of the flowfield details, but the general characteristics of the flowfield remained the same, provided a threshold of approximately 3000 crossflow grid cells was exceeded. The flow solutions were also found to be relatively insensitive to variations in artificial viscosity. The predicted strength of leadingedge vortices generally increased with increasing angle of attack, streamwise station, and Mach number.
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