Aerodynamic Performance as a Function of Local Twist in an Unmanned Airplane

Abstract

Recently published works predict that any planform shape may be optimized with twist to reduce the induced drag to an optimum value. The objective of this paper is to observe how the distance between the wing root and the twist start line is linked to the maximum lift –drag ratio and to the maximum lift co efficient on an unmanned aerial vehicle designed for the early detection of oil leakages in the extraction areas. The aerodynamic analysis was performed using a panel code to compute the inviscid flowfield, a viscous drag built to estimate the viscous drag , and the pressure difference rule to calculate the maximum lift coefficient. The results show that the maximum lift –drag ratio increases and the maximum lift coefficient reduces as the distance between the wing root and the twist start line decreases. The lift –drag ratio increases 1.51%, and the maximum lift coefficient decreases 3.55% respect to the value for the untwisted airplane. The twist start line was placed at 0.815 m as the greatest lift –drag ratio augmentation is located at this station. The res ults demonstrate that the maximum lift –drag ratio and the maximum lift coefficient are linked to the distance between the wing root and the twist start line.