first connection device 40 is here the front area 31 or inlet area while the area in relation to the direction of flow in the gap before the second connection device 50 is the rear area 33 or outlet area as a result the first connection device 40 is the location of the inlet area or the front area 31 of the skin section 30 in relation to the wing chord direction of the aerodynamic body 10 by contrast meaning in the second connection device 50 the rear area 33 of the skin section 30 or outlet area for the airflow is located in the gap between the aerodynamic body 10 and main wing 100 if the aerodynamic body 10 has been completely deployed it is advantageous that the shedding of turbulent eddies be reduced or avoided in proximity to the connection device 40 meaning in the inlet area in the gap between the aerodynamic body 10 and main wing 100 so as to prevent noise emission and or vibration to this end the skin section 30 is moved into a position as depicted on fig1 b this position is referred to as the folded out dimensional state 34 of the skin section 30 this folding out process enlarges a cavity 62 between the skin section 30 and rear side 24 of the main body structure 22 as shown by a comparison of fig1 a and 1 b the latter differ predominantly by the cross sectional contour of the skin section 30 when the skin section 30 is in the folded in dimensional state 32 as shown on fig1 a it is provided exclusively with a concave curvature between the connection device 40 in the front area 31 and.