An unmanned air-vehicle with deployable components, UAVDC, comprising: a fuselage; a wing arrangement segmented in a left wing section and a right wing section to enable variable sweep at approximately a lateral plane of symmetry between the left wing section and the right wing section, the wing arrangement being configurable in a first arrangement, a second arrangement, and a third arrangement, wherein the first arrangement comprises the left wing section and the right wing section stowed against the fuselage at a first sweep deployment angle, wherein the second arrangement comprises the wing arrangement fully deployed for flight at a second sweep deployment angle, and wherein the third arrangement comprises the wing arrangement deployed in any sweep deployment angle between the first sweep deployment angle and the second sweep deployment angle; and a sweeping means (205, 210) configured to pivot the left wing section and the right wing section to enable the wing arrangement to sweep from the first arrangement to the second arrangement at any sweep deployment angle, wherein the sweeping means is covered by a fairing positioned at a root of the left wing section and the right wing section, the fairing comprising at least one slit and at least one cutout, characterized in that the fairing is constructed of a flexible material and is configured to flex at a location of the at least one slit to accommodate the left wing section and the right wing section in the first arrangement; the fairing being configured to: open by flexing to allow the left wing section and the right wing section to be stowed under the fairing in the first arrangement, and close to provide aerodynamic advantage in the second arrangement; and wherein the fairing does not flex at the location of the at least one slit to accommodate the second arrangement. a fuselage; a wing arrangement segmented in a left wing section and a right wing section to enable variable sweep at approximately a lateral plane of symmetry between the left wing section and the right wing section, the wing arrangement being configurable in a first arrangement, a second arrangement, and a third arrangement, wherein the first arrangement comprises the left wing section and the right wing section stowed against the fuselage at a first sweep deployment angle, wherein the second arrangement comprises the wing arrangement fully deployed for flight at a second sweep deployment angle, and wherein the third arrangement comprises the wing arrangement deployed in any sweep deployment angle between the first sweep deployment angle and the second sweep deployment angle; and wherein the first arrangement comprises the left wing section and the right wing section stowed against the fuselage at a first sweep deployment angle, wherein the second arrangement comprises the wing arrangement fully deployed for flight at a second sweep deployment angle, and wherein the third arrangement comprises the wing arrangement deployed in any sweep deployment angle between the first sweep deployment angle and the second sweep deployment angle; and a sweeping means (205, 210) configured to pivot the left wing section and the right wing section to enable the wing arrangement to sweep from the first arrangement to the second arrangement at any sweep deployment angle, wherein the sweeping means is covered by a fairing positioned at a root of the left wing section and the right wing section, the fairing comprising at least one slit and at least one cutout, characterized in that the fairing is constructed of a flexible material and is configured to flex at a location of the at least one slit to accommodate the left wing section and the right wing section in the first arrangement; the fairing being configured to: open by flexing to allow the left wing section and the right wing section to be stowed under the fairing in the first arrangement, and close to provide aerodynamic advantage in the second arrangement; and wherein the fairing does not flex at the location of the at least one slit to accommodate the second arrangement. open by flexing to allow the left wing section and the right wing section to be stowed under the fairing in the first arrangement, and close to provide aerodynamic advantage in the second arrangement; and wherein the fairing does not flex at the location of the at least one slit to accommodate the second arrangement.