Aircraft comprising an aircraft light unit, wherein the aircraft light unit is a forward navigation light unit, wherein the aircraft light unit comprises: a support portion, a light source having at least one LED, the light source being arranged on the support portion and in operation emitting light with a source-side light intensity distribution, and an optical element for transforming the source-side light intensity distribution into an output light intensity distribution, wherein the optical element has at least two transformation segments (10, 20, 30), covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane, the at least two transformation segments (10, 20, 30) comprising: a first transformation segment configured so that the light from the light source experiences total internal reflection within the optical element in the first transformation segment and is bundled in a peak region of the output light intensity distribution, wherein the first transformation segment covers an angular range of between 20° and 40° of the source-side light intensity distribution in the first cross-sectional plane and wherein said peak region in the output light intensity distribution has an opening angle of between 5° and 15° in the first cross-sectional plane, and wherein said peak region in the output light intensity distribution coincides with the forward navigation direction of the aircraft; and at least one further transformation segment (20,30) configured so that the light from the light source experiences refraction only in the at least one further transformation segment (20, 30), wherein the aircraft light unit is disposed in a wing tip region of the aircraft; and wherein the aircraft light unit is arranged in such a way that a principal light emission direction of the light source is at an angle of between 20° and 40° with respect to the longitudinal direction of the aircraft body. a support portion, a light source having at least one LED, the light source being arranged on the support portion and in operation emitting light with a source-side light intensity distribution, and an optical element for transforming the source-side light intensity distribution into an output light intensity distribution, wherein the optical element has at least two transformation segments (10, 20, 30), covering different angular ranges of the source-side light intensity distribution in a first cross-sectional plane, the at least two transformation segments (10, 20, 30) comprising: a first transformation segment configured so that the light from the light source experiences total internal reflection within the optical element in the first transformation segment and is bundled in a peak region of the output light intensity distribution, wherein the first transformation segment covers an angular range of between 20° and 40° of the source-side light intensity distribution in the first cross-sectional plane and wherein said peak region in the output light intensity distribution has an opening angle of between 5° and 15° in the first cross-sectional plane, and wherein said peak region in the output light intensity distribution coincides with the forward navigation direction of the aircraft; and at least one further transformation segment (20,30) configured so that the light from the light source experiences refraction only in the at least one further transformation segment (20, 30), a first transformation segment configured so that the light from the light source experiences total internal reflection within the optical element in the first transformation segment and is bundled in a peak region of the output light intensity distribution, wherein the first transformation segment covers an angular range of between 20° and 40° of the source-side light intensity distribution in the first cross-sectional plane and wherein said peak region in the output light intensity distribution has an opening angle of between 5° and 15° in the first cross-sectional plane, and wherein said peak region in the output light intensity distribution coincides with the forward navigation direction of the aircraft; and at least one further transformation segment (20,30) configured so that the light from the light source experiences refraction only in the at least one further transformation segment (20, 30), wherein the aircraft light unit is disposed in a wing tip region of the aircraft; and wherein the aircraft light unit is arranged in such a way that a principal light emission direction of the light source is at an angle of between 20° and 40° with respect to the longitudinal direction of the aircraft body.