EXPERIMENTAL AND COMPUTATIONAL STUDY OF TWO FLAPPED AIRFOILS AT LOW REYNOLDS NUMBERS

摘要

In this work, two different airfoils, NACA 2412 and SD 7062, with plain flaps, were tested experimentally at a low Reynolds number range typical for Unmanned Aerial Vehicles. The measured results were then compared with a handbook method presented by Roskam and CFD codes, XFOIL, and FINFLO. The purpose of this work was to study the effect of low Reynolds number and flaps, as well as the capability of the studied methods to predict these effects.