Aircraft conformal windows have asymmetrical shape and usually tilt relative to the imaging system behind. Thus, rotationally symmetrical fixed corrector having the simplest structure can not be applied to aberration correction for aircraft conformal windows. To simplify the structure of aircraft conformal correction system to the greatest extent, the two-stage static correction of aircraft conformal window aberration is presented. This solution makes fixed corrector applied to the aberration correction for aircraft conformal windows. The first stage static correction is to correct the asymmetrical aberration introduced by the conformal window at 0° field of regard along the axis based on some static correction method. This stage provides condition for using fixed corrector. It is proved theoretically that the first stage static correction can be achieved by designing the inner surface of the conformal window. The second static correction is to correct the dynamic aberration varying with the look angle introduced by the conformal window using fixed corrector. The two-stage static correction principle of aircraft conformal window aberration is clarified. Based on this principle, a design example is presented.