Abstract

 
 
 The aerodynamic performance of low Reynolds airfoils with a Reynolds number less than 105 is critical for a variety of applications, including unmanned aerial vehicles, micro air vehicles, and low-speed/high-altitude aircraft. In general, most airfoils with Reynolds numbers less than 106 cannot be considered to have constant lift and drag characteristics. XFLR5 is a tool for analysing low-Reynolds-number airfoils, wings, and aircraft. It comes with XFOIL's direct and inverse analysis tools. The lifting line theory, the vortex lattice approach, and the 3-D panel method are all used to build and analyse wings. The lift coefficient (Cl) and pressure distribution (Cp) are fundamental metrics that determine the behaviour of airfoils. The cornerstone of aerodynamic analysis during aircraft development is pressure distribution data.
 
 
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