The way to achieve minimum induced drag (even for a modern fighter) is to have an elliptical lift distribution. A well-designed fuselage will "carry through" the wing lift with little or no dip in the lift distribution. This means that the most efficient fuselage will actually generate more lift per unit span than the wing.

That said, most fuselages would generate very little lift in the absence of the wing. Consider that wingtips themselves rarely generate much lift, but without the wingtips, the lift generated by the rest of the wing would be significantly less.

In the case of the F-15 with the missing wing, the lift on the "missing" side was generated mostly by the stabilator. If you were to try to create lift with the fuselage, you would load up the remaining wing an cause the aircraft to roll (unless you could completely "null out" the wing lift with aileron). If you estimate maximum lift coefficient of the F-15 stabilator and combine it with the area, you can determine the minimum landing speed for a given gross weight. For the case in question, this estimate comes out pretty close to the reported landing speed.

I don't think I would want to land on the boat minus a wing.