Investigation of the Design and Application for the Two Element Airfoil of Medium Altitude Long Endurance UAV

Abstract

According to the design requirements related to high endurance factor, short take-off and landing, deforming resistance of medium altitude long endurance(MALE)UAV, the investigation of the design methodology on multi-constraint of the two-element airfoil is conducted based upon the earlier studies of the one-element airfoil design.The geometry of the two-element airfoil is generated with the method of controllable conic curves accompanied with the control points.Meanwhile optimum design of the UAV inner wing is carried out using the designed slot airfoil and improvement effect is evaluated.The results indicate that the endurance factor, take-off lift and lift-to-drag ratio of the optimum UAV are substantially improved.At the same time, the drag of full flap increases under the certain lift conditions which is beneficial to the landing deceleration.This method can meet the requirements such as the efficient cruise, short take off and landing and is significant to the MALE UAV design.

Keywords

• male uav
• high lift-to-drag ratio
• airfoil design
• two-element airfoil