An aerodynamic performance study and analysis of SD7037 fixed wing UAV airfoil

Abstract

This work presents an investigation of aerodynamic characteristics of SD7037 low Reynolds number fixed win UAV airfoil. In this work the model design considerations of SD7037 low Reynolds number airfoil has been used to design and analysis. The model design parameters are consistent for the evaluation of aircraft performance and data are recomputed. The aircraft aerodynamic induced drag factor is selected as a parameter for design method and this has been approximately calculated for the airfoil and wing characteristic curves. The results gained by analysis from the designed airframe are suitable for the soft computing requirements. The calculated performance aspects came to be desirable and the soft computing techniques and feature detection program successfully differentiated between the runway and other objects to test automatic take off and landing of UAV. As planned the test for stability of the UAV was performed successfully and the model was self-stabilizing it-self.