This thesis is based on the application of the Pitot system in aviation. The design and performance features, components and operating principle of the Pitot-static system will be described in detail. In the introduction are given historic information of the inventors of Pitot-static tubes and their origin. The second chapter explains the theoretical background necessary to understand the operation of the Pitot and Pitot-static tubes with the equations necessary for obtaining velocities when measuring pressure, while the third chapter describes the measurement of mass and volume flow in the pipeline using the pressure difference. In the fourth chapter, the principle operation of the Pitot-static system in aircraft and installation systems in modern aircraft is explained in detail. Chapter five will present the principle of measuring fluid velocity using Pitot-static tubes in the Virtual Wind Tunnel software and graphical representations of the pressure field and velocity around the Pitot-static tube. Finally, the air flow velocity behind the aircraft wing will be conducted in the AF100 Subsonic Wind Tunnel. The test will be proven with a wing with an angle of attack of 0° and then with an angle of attack of 45°. The results obtained using the air tunnel will be displayed graphically using the AcuFieldView softwar