An aerodynamic pressure sensing system for an such as an airplane lifting surface, rotor blade etc. is disclosed wherein a plurality of pressure probes (7) are arranged on the upper and lower surfaces of the airfoil-shaped body (1) to sense aerodynamic pressure at discrete locations thereof, wherein the pressure sensitive elements (7) are arranged to form a plurality of rows (8) on said upper and lower surfaces. According to the invention between 55-75% of the total number of the pressure sensitive elements (7) are arranged at the leading edge section, and the remaining pressure sensitive elements are arranged at the intermediate section of the airfoil-shaped body. The invention allows measuring aerodynamic forces generated at the leading edge of the airfoil and particularly the suction peak more precisely and with a reduced number of pressure probes.