Aircraft wing with an upper surface element and a first actuator powered mechanism for varying a shape of the upper surface element, wherein - the upper surface element is an adaptive shock control bump and comprises: ∘ an upstream segment SEG 1 with a stiffness S 1, ∘ a downstream segment SEG 2 with a stiffness S 2, ∘ an interconnecting segment SEG 3 with a stiffness S 3, the interconnecting segment SEG 3 is interconnecting a downstream edge of SEG 1 with an upstream edge of SEG 2, wherein the interconnecting segment SEG 3 is extending along the whole downstream edge of SEG 1 and the whole upstream edge of SEG 2, or at least along a major part of the downstream edge of SEG 1 and a major part of the upstream edge of SEG 2, wherein the stiffness of each of SEG 1 and SEG 2 is greater than the stiffness of SEG 3, ∘ a link element LNK, the link element LNK is interconnecting an upstream edge of SEG 1 with an upper surface of the aircraft wing, the interconnecting element SEG 3 exhibiting a mechanical pretension causing the upper surface element to exhibit in a reference status a convex shape with a maximum bump height BH max; and the first actuator powered mechanism is interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the aircraft wing, wherein the first actuator powered mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2, such that a pulling force is applied to the upper surface element by reducing a distance between C1 and C2. - the upper surface element is an adaptive shock control bump and comprises: ∘ an upstream segment SEG 1 with a stiffness S 1, ∘ a downstream segment SEG 2 with a stiffness S 2, ∘ an interconnecting segment SEG 3 with a stiffness S 3, the interconnecting segment SEG 3 is interconnecting a downstream edge of SEG 1 with an upstream edge of SEG 2, wherein the interconnecting segment SEG 3 is extending along the whole downstream edge of SEG 1 and the whole upstream edge of SEG 2, or at least along a major part of the downstream edge of SEG 1 and a major part of the upstream edge of SEG 2, wherein the stiffness of each of SEG 1 and SEG 2 is greater than the stiffness of SEG 3, ∘ a link element LNK, the link element LNK is interconnecting an upstream edge of SEG 1 with an upper surface of the aircraft wing, the interconnecting element SEG 3 exhibiting a mechanical pretension causing the upper surface element to exhibit in a reference status a convex shape with a maximum bump height BH max; and the first actuator powered mechanism is interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the aircraft wing, wherein the first actuator powered mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2, such that a pulling force is applied to the upper surface element by reducing a distance between C1 and C2. ∘ an upstream segment SEG 1 with a stiffness S 1, ∘ a downstream segment SEG 2 with a stiffness S 2, ∘ an interconnecting segment SEG 3 with a stiffness S 3, the interconnecting segment SEG 3 is interconnecting a downstream edge of SEG 1 with an upstream edge of SEG 2, wherein the interconnecting segment SEG 3 is extending along the whole downstream edge of SEG 1 and the whole upstream edge of SEG 2, or at least along a major part of the downstream edge of SEG 1 and a major part of the upstream edge of SEG 2, wherein the stiffness of each of SEG 1 and SEG 2 is greater than the stiffness of SEG 3, ∘ a link element LNK, the link element LNK is interconnecting an upstream edge of SEG 1 with an upper surface of the aircraft wing, the interconnecting element SEG 3 exhibiting a mechanical pretension causing the upper surface element to exhibit in a reference status a convex shape with a maximum bump height BH max; and