Fast Airfoil Selection Methodology for Small Unmanned Aerial Vehicles

The purpose of this study is to fill the gap that exists when applying the airfoil selection methodology according to the textbooks that appear in the above featured application section, in the low Reynolds number segment, by providing useful data. Data acquisition software was XFLR5. The major result is the construction of a prototype maximum lift coefficient versus ideal lift coefficient diagram, or $\left(C_{l_{max}}-C_{l_i}\right)$ diagram, composed exclusively of low Reynolds number airfoils. In addition, the necessary supplementary airfoil characteristics’ tables are provided, for conducting fast airfoil selection for Small Unmanned Aerial Vehicles (SUAVs). As a conclusion by implementing the proposed methodology, the SUAV designer is disengaged from the time-consuming process of the construction of similar $C_{l_{max}}-C_{l_i}$ diagrams and supplementary characteristic tables and the airfoil selection-processing time can be greatly shortened, because the main work of the process is reflected by the current findings. To express the time gain in a percentage manner, authors estimate that 85% of engineering time will be economized in the overall airfoil selection procedure if the current findings are used, due to the fact that no new airfoil simulations are required. Finally, candidate SUAV designers are encouraged to expand the airfoil database, according to the proposed methodology.