Aerodynamic analysis of a complex configuration using a full potential code

A detailed comparison between supersonic full potential calculations and experimental surf ace pressures and force and moment coefficients for the F111/TACT configuration at Mach numbers of 1.6 and 2.1 has been performed. The agreement between the predicted and measured surface pressure distributions, the lift curve slope and the lift-todrag ratio was good to excellent. The zero-lift pitching moment for both Mach numbers examined was underpredicted. The drag polar for Mach 1.6 was in good agreement with experiment. For Mach 2.1 the drag was underpredicted by about forty counts but the shape of the polar was in good agreement with experiment. The disagreement between the predicted and measured zero-lift pitching moments and drag levels was attributed to the use of actual geometry rather than the distorted configuration required for incorporation of the wind tunnel sting.