A combined experimental and numerical analysis of UAV Pitot-static system error at low Reynolds number

This paper describes how the placement of a Pitot static probe on an airfoil affects the Pitot static system error which arises due to viscous effects extending from the leading edge of the airfoil and probe. The airfoil of interest for this study is a Clark Y airfoil with a 0.3048 m chord length set to a 0 degree angle of attack. Wind tunnel testing and 3D numerical simulations using ANSYS CFX were used to analyze Pitot static probe measurements for a probe extending forward of the airfoil chord line from 0 to 20 cm at Reynolds numbers from 1 × 10⁵ to 5 × 10⁵. The results obtained demonstrate how probe placement and Reynolds number affect the measured stagnation and static pressure which are used in determining velocity and altitude.