F-lll TACT tests at M- 0.9 and a = 6 deg showed severe wing unloading in the inboard region over the glove and fuselage, and a shock wave unsweeping in the tip region deteriorating the cruise performance. A computational model is developed for use on the Bailey-Ballhaus transonic small-disturbance code which allows a good simulation of the complex fuselage geometry, including inlet effects, of the F-lll TACT. Comparisons with experiments show good agreement. Fixes are demonstrated which alleviate some of the aerodynamic deficiencies of the original aircraft. Nomenclature c = local wing chord Cp = pressure coefficient M = freestream Mach number n = surface unit normal vector t — thickness V - total velocity Vil ^oo = inlet velocity ratio WBL = wing butt line x = chordwise body axis coordinate y = spanwise body axis coordinate z = body axis coordinate normal to x-y plane a = angle of attack rj — span fraction